Wind tunnel test of the Thomas-Morse MB-3 airplane (Airplane Section report)

              ING
Auburn University Libraries
11111111m~1111m~~
NON· \. 3 1706 025 85024 4
File D S2.l / Thomas Morse/37
AIR SERVICE IN A TION CIRCULAR
<AVIATION)
PUBLISHED BY THE CHIEF OF AIR SERVICE. WASHINGTON, D. C.
Vol. V June 1, 1924 No. 468
WIND TUNNEL TEST OF
THE .THOMAS-MORSE MB-3 AIRPLANE
(AIRPLANE SECTION REPORT)
Prepared by
A. L. Morse, Engineering Division, Air Service
· McCook Field, Dayton, Ohio
March 14, 1924
WASHINGTON
GOVERNMENT PRINTING OFFICE
1924
CERTIFICATE: By direction of the Secretary of War the matter contained
herein is published as administrative information and is required for the proper
transaction .of the public business.
(n)
r
•
WIND TUNNEL TEST OF THE THOMAS-MORSE MB-3
AIRPLANE
NoTE.-This report includes wind tunnel tests of the original MB-3 and three modifications: (a) With
the new tail surfaces designed by the Engineering Division; (b) With the new tail surfaces and with the fuselage
lengthened lYs feet, and (c) With the new tail surfaces and with the. fu sehurn lengthened 2 feet.
OBJECT
The object of these tests is to determine the aero­dynamic
characteristics of the Thomas-Morse MB- 3
airplane.
DATE AND PLACE
The Thomas-Morse MB- 3 airplane with the above
modifications was tested in the Massachusetts Institute
of Technology 4-foot wind tunnel at Cambridge, Mass.,
except as noted below, on the following dates:
Date
Sept. 27, 1922 _____ _
May, 1922 ____ ____ _
September, 1922. __
Sept. 12 and 13,
1922.
Sept. 21 , 1922 _____ _
Sept. 25, 1922 __ ___ _
Sept . 27, 1922. ____ _
Mar. 21, 1923 __ ___ _
Mar. 21, 1923 _____ _
Oct. 30, 1923 ______ _
Test
Mc. g. without tail for all conditions.
L, D, L/D , X, .Z, and Mc. g. as originally designed.
Angle of stabilizer cbord to thrust line=0°.
Angle of elevator to stabilizer cbord=+30°, 0°,
-30°.
L, D, L/D, X, Z, and Mc. g. witb new tail surfaces
· and with tbe fuselage lengthened l)i feet. Angle
of stabilizer chord to thrust line=+Y.0
• Angle of
elevator to stabilizer chord=+20°, 0°, -20°.
L, D, L/D, X, Z, and Mc. g. with new tail surfaces
and with the fuselage lengthened l )i feet. Ang1e
of stabilizer chord to thrust line=+Y.0
• Angle of
elevat or cbord to stabilizer=+20°, 0°, -20°.
L, D L/D, X, Z, and Mc. g. with new tail surfaces
and with fuselage lengthened 2 feet. Angle of
stabilizer chord to thrust line=+Y.0
• Angle of
elevator cbord to stabilizer=+20°, 0°, -20°.
Lateral force and yawing moment about c. g. witb
new tail surfaces designed by tbe Engineering
Division; witb new tail surfaces and fuselage
lengthened !Ji feet; with new tail surfaces and
fuselage lengthened 2 feet.
Rudder moments about c. g. with new tail sur­.
faces designed by the Engineering Division;
witb new tail surfaces and fuselage lengthened
!Ji feet; and with new tail surfaces and fuselage
lengthened 2 feet. ·
L, D, L/D, and Mc. g. of wing cell without tbe rest
of tbe model.
Le, De, L/D, and c. p. of Thomas-Morse MB-3
upper -wing alone.
Lift and drag on 78 scale model of fuselage and
chassis alone. Tested in McCook Field 5-foot
wind tunnel.
DESCRIPTION
The Thomas-Morse MB- 3, Type I, is a single­seater
pursuit biplane powered with a Hispano-Suiza
. 300-horsepower motor. The model was made of wood
with brass struts. The characteristics are given below.
Model: Thomas-Morse MB- 3 single-seater pursuit.
Type I.
Scale: -h size.
Material: Model, wood with brass struts.
Dimensional accuracy: ro-t0 -inch wings, rh-inch
fuselage.
Where tested: M. I. T.
Wind speed: 30 m. p. h.
Overall length (1): 20 feet.
Overall span (S): 26 feet.
Overall height: 7 feet 8 inches.
Horsepower: 330.
Weight fully loaded: 2,485 pounds.
Power loading: 7.53 pounds per horsepower.
Wing loading: 10.85 pounds per square foot.
Location of c. g. on model is as follows: ,
(1) As originally designed 1.31 inches aft of L.
E. of lower wing; 0.33 inch above thrust
line; 33.15 per cent of M. A. C.
(2) With new tail surfaces designed by the
Engineering Division; 1.43 inches aft of
L. E. of lower wing; 0.90 inch above
thrust line; 36.21 per cent of M. A. C.
(3) With new tail surfaces and with the fuse­lage
lengthened lYs feet or 1 inch on
model; 1.52 inches aft of L. E. of
lower wing; 0.90 inch above thrust line;
38.50 per cent of M. A. C.
(4) With new tail surfaces and with the fuselage
lengthened 2 feet or 1.5 inches on model;
1.56 inches aft of L. E . of lower wing;
0.90 inch above thrust line; 39.50 per
cent of M. A. C . .
WINGS
Type: The wings of the MB- 3 are of the two bay
biplane type with an enlarged portion of the outer
section for tank space. Ailerons on upper wings only.
Section: RAF- 15.
Gap: 53.75 inches.
Stagger : None.
Total lift area: 228 square feet.
Mean aerodynamic chord: 63 3/16 inches.
Area, including ailerons __ _
Overall span ________ ___ __ _
Effective span ____ -- ------
area
Mean chord~ span _______ _
Aspect ratio ____ ______ ___ _
Angle of incidence at root _
Angle of incidence at t ip __
Dihedral_ ___ __ ___________ _
(1)
Upper Wing Lower vVing
124.05 square feet_ ___ 104.50 square feet.
26 feet_ _______ ____ ___ 24 feet 6 inches.
26 feet _______________ 21 feet.
4.77 feet= 57.3 inches_ 4.97 feet=59.6 inches.
5.45 _________________ 4.95.
+30 - ----------- - ---- -40'.
-40' ---- - - - - - ------- -40'.
30 --- - - - - - - --- -- -- --- 30.
--~~~~~~---'--(' :::::..~~~~--------------
•
1
1 ~!:~tc~~~~-;f-~l~~~;;;; b~~k-~f hl~1~~== = = = = = = = ~: ~~
AILERONS Percentage of elevator chord to horizontal tail
The ailerons are of the usual unbalanced type surface chord _ - -. - - - - - - - - ~ - - - - - - - - - - - - - ~ - - 33. 1
CONTROLS
T ype:
on the upper wing only .
T otal aileron area: 19.68 square feet.
Span of each aileron: 6 feet 6 inches.
Mean aileron cho rd= area = 1.5 feet= 1 foot
span
6
inches= 18 inches.
P ercentage of mean aileron chord to wing chord= I
28.5 p er cent.
P ercentage of aileron area to >ving a rea (a) = 8 .63 per
c ~ nt .
aS =42.5.
c
HORIZONTAL TAIL SURFACES
\a) As originally designed.
T ype: The horizontal tail s urfaces are of t he
usual end-balanced type, having a symmet-rical
section.
Section: See Figure 9.
Area of stabilizer_ ___ _____ ____ __ square feet_ _ 9. 12
Area of elevator back of hinge _______ ___ do ___ -
Area of elevator balance _____________ __ do __ _ _
T otal elevator area __________ ____ _____ do __ _ _
Total horizontal tail area ______________ do ___ _
Span ____ ____ __ _____ __________ ____ ___ feet __
Me9.n horizontal tail surface chord ___ __ do ___ -
Aspect ratio ____ ____________ ______ ___ ____ _ -
14. 45
2. 55
17. 00
26. 12
8. 83
2. 96
2. 99
MeJ.n chord of elevator back of hinge ___ _ fect__ 1. 64
P ercentage of elevator chord to horizontal tail
surface chord _______ _____ ___ - ___ - - - __ __ _ - 55. 5
Percentage of horizontal tail surface to wing
area (hl --- - -- ---- - - - ----- - --c--- - ------ - 11. 45
Number of wing chord lengths from c. g. to ele-vator
hinge (t ,)_ ___________ _______ _____ _ · __ 2. 37
Vertical location of horizontal tail surface with
respect to wings in terms of t he wing chord
lengths below upper wing____ __ __________ __ . 38
t,h ___________ ____ _________________ _______ _ 2~ 15
C. g. position in per cent of chord__ ________ __ 33. 2C
(b) With t he new tail surfaces designed by t he E ngi­neering
Division.
(c) With tile fuselage lengthened l Ya feet.
(d) With t he fuselage lengthened 2 feet.
T ype : The new tail surfaces were of t he same
type as the old. The a spect ratio was in­creased
and t he elevator chord was decreased .
Percentage of horizontal tail surface to wmg
area (h) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 14. 65
Vert ical location of horizontal tail surface with
respect to wings in terms of chord (below
upper wing) __________________________ ___ .38C
Case b Case c Case d
--- -------- ----- - - - --- --- -
Value of (I,) _____ ____________________ __ _
t,h __ - -- -- --- - ---- --- ----- - -- -- ------- -- -
c. g. position in per cent of ch_ora __ ____ _ _
2.34C
34. 3
36.3C
VERTICAL TAIL SURFACES
(a) As originally designe<l.
2.32C
34. 0
38. 6C
2.3 1C
33. 8
39. 6C
T ype : The vertical tail surfaces are of the
usual type with a balanced rudder.
Section: The section used may be seen on the
three view drawing, Figure 4.
Area of fin ___ _________________ square feet__ 1. 55
Area of rudder back of hinge ____ ____ _ do __ __ 7. 02
Ba lanced area __ ___ _________________ do __ _ _
Total rudder area ___ _______ _________ do __ _ Total vertical tail s urface area __ _____ do ___ _
P ercentage of total vertical surface area to
wing area (v) ____________ ______ ________ _
N'umber of wing chord lengths from c. g. to
rudder hinge (t2) - _ _ - - - - - - - - - - - - - - - - - - - - -
. 612
7. 632
9. 182
4. 02
2. 55C
t
2
v __ _______ ____ ________________ _ - _ _ _ _ _ 10. 25
(b) With new tail surfaces designed by the Engi­neering
Division.
(c) With the fuselage lengthened 1.H feet.
(d) With the fuselage lengthened 2 feet.
T ype : The new vertical tail s urfaces are
similar to the original vertical tail surfaces .
The ratio of fin a rea to ver t ical tail area is
increased .
Section: See Figure 10.
Area of fin __ ______ __ _____ ______ squa re feet_ _
Area of rudder back of hinge ___________ do __ _ _
Area of rudder balance ____________ ____ do ___ I Total rudder area __ _____________ __ ___ do ~ __ Total vertical surface a rea __ ~ _____ _____ do ___ _
Percentage of total vertical surface area to wing
area (v) ________________ _______ - _____ __ _ _
5. 15
5. 70
30
6. 00
11. 15
4. 89
Sect ion: Gottingen 409. See Figure 11.
Area of stabilizer _____ _____ ___ __ sq uare feet_ - 21. 50 Case b \ Case c Case d
Area of elevator back of hinge _____ ____ do ___ _ 11. 09 '--------- ----1---- --- - - -
Area of elevator balance ____ __ __ · ____ __ do __ _ _
Total elevator area ___ ____ _________ ___ do ___ _
Total horizontal tail area _______ ____ ~ __ do ___ -
Span ____ ___ ________ _________ ____ __ __ feet __
Mean horizontal tail surface chord ______ do ___ _
83 Valueof(l2)_____ __________________ ___ __ 2.52C I 2.50C 2.49C
· t2v. _ __ __ __ __ _ __ _ _____ ___________ __ _ _ 12. 31 12. 23 12. ·18
11. 92
33. 42
10. 82 I
3. 09
The fuselage model was made of wood with brass
struts and was dimensionally correct to 1/100 inch.
J
r.
i !
l
,~
'
\ ..
I
!
lit
L __,
- - .. - I 1
' - - ..
r---~-r- - r \ i -...I;
tl~ u 11 F\~L
\ . I \
~
."\. I
'· « ~
t • ~ !
\ f ~
- ~
I ' J ~
- ..
l J
, ... _
=
'-..,-!
·1 ;~ ' ~ ' .,.
1·--f--~--~ -.....!)· ' 'f . ~ ... ..s
f, ·'· I'
/
I .•
i-----""'f- ' 1;
'1: j "'
1· I I :
'"' _...,.........
~ ,11
~ J ~
~ & 11I ' '
1
~ ! ~ .... ~
"'
...__ __ _ -
\. I
3•
2 . ?-00
/,J7c:;~
/.S'J'S
/./8/
.?aa
.59 /
i• F" ()l Ii) l() I) ~
~~ ~ ~ ~ ~ ~
~~ ~ ,. . ' ...; ...;
~ ~
l I
~ ao· t
~
""'
Lo vvER £:0 ~E o,,. 7,e;,..,,o,1.ifr£
OouB.t.I!!: Snt.E:
~
~
"
.t.. .r.e.
I)·
t... ...,
:!
.f.f.
:----!I"· ........~ ~-~ -----;:--..:;·- ----------·----;--_-f-----..·-----~ ._ ____... ....
~
I') ....
~
I• NoR,~. PRt:1.r. 5. 'i' 38 - -------------i
I
Hd~IZO.IVTA.L L NV6
~ THo.,..,,.,s /'?oRs.E·/'?B-3
~ Secr/o/V A·.lf
. /'?· :ZS BIJ
3•
.Re r1n•1.. S'z~
/VE
IYqrct-
~
~
CoRNE"7 AIV£'-eS o,. 'TA:,..,P.LA7E
ARE NOT 90°
AIR SERVICE
£M61NEE~1N6 01".
/
FIG.5
Te/'1,..J.ATIE F'OR W"vf"
OIV;,. M-25~1!> 'DDEJ..
.,
01
I \
~-------------- 3,:l!J0'------------1 . c 3.15"
I 2.rs?-·--------1
r HoR 1:z.. PRaJ: S. 9 38 ----..,.----------___,.,
~.3~3--------1
""--------/.9<.p---·- ------r
.?aa
. .59/
.39.,.
''" f'I ' .... "''°'" ...... . l'IN Ii N N
'..:-s ..... ~ ....
/.$75_
/ ./81 ------i
~
.'.. , ...
~
.(.',(
-a
.~..,
ri
"
.~., ...
~
,N.
Low~:R E'oG>E o..- 'TE,.,PL11tr.
·~s I/ (llGOl'lLL llYT&t-1./Jll'!S.1Di?9<1 E.J.I/.
'
l'f
,~.
g:
N
""
@
~°' ....
~
.!.'.f
OollBI.£ S14E
0. .:..,
~
.N...
.~. ....
: ,f'f.
QI
,~.
t t
N f'l
....: ....:
~N
(':-(
~
I') '
...
~
3•
\
7i-ta/>'1AS /"1aR:s':.:":18-\3
S~CTIO/Y 813~
M-2589
1.,,z-f i
I --=- ...... It:"
~ 5Tl'f/'1P,'-
ACTVAL S1Zlf
/Vqre.:-
CaRNEfl AIVqL..!".S o, TEMPLATE
ARE /llOT 9o•
,,.
A IR ScR\l\Cf:-17£,.,PJ..ATF FoR Wnvf" Sccr10N 88
t.MGltil?:r-RJi-1<0 ow. ON 7NoMAS .1"?0R11£ MS-3 /'?oDE.1. . l'?-2.589 '
l'w. 6
'-)
O')
.....
0
C.n
0
I'° .t,V.
I
-f'.
'
I :3.938 ~
: ,;:,+/ :;:-1 I f<oR•~ PRo.& <9'8 1
3.1.So ~-'r-------------------------~ - --- · 2.f'.5,,. - ----- ---- .....,
t- l .9ro9 ~- 3w3
M------1 5 '75 _____ ____,..,
14-----~I 81
.788
.SW
.391'-
:: ~
,'}. ,,, -..:
'"i:t ~(Q~ ~ -~ ~
"•~ l'?ri"I t'1 N N ~
I&
~ -.:
-~
!'I
~ s .,.
~ ..,:
~ ~
~ N
l
"' ~-
"
~
N
a°t")
~
~
:,I'(
("(
L
I
"l " '° l'I ~
.'t.,-: .t.. . ~-
~
I
."\.I,"I
"
,I..),
"
1--
lso1: :f
HoRlzalYTAL L1N&: ~
THON AS /1'7oRSE /"1-8- 3
SECTION C-C '
/"'1-2 590 """
ACTlHIJ. SIZE
NorE.'-
~57."IMP:-
' x...:~- ...._. - · " t'I
11tlH ! ! I,! !® L t t ! f ! N
t.. .
i..
N
LoYV£/!l Eo-;E o~ T~MPLllrE: 1
DousLE Size:
'148j A · CNtlJ'9L~ lltTOi'l"l.D/,#!S.Amr/ EJ(.I
o~,.'TS,f"TC.t-1 biw"t' ... f"f'~"~O
AIR SERVICE.I TEMP.I.AT~ F4'R WNY~ SEC'TIO/Y C'·C I 1'1-25 961
11: .. ~INH"''"'-4 01\/. otv THo,.,As NoRsl: /"1 B-3-l"foDl!L.
F IG.
-..1
If+ f1i i i t J. • ·
~ ::: ' ~ ~ ;o-' Ill ~ g: ~
J~ ~ ~!~ i~ l~ l~ ~ ~ ~ ~ . •®
LollVER E:o E or NPL TE
' DouSJ..E Snr.I!!!;
11748¢ .4 C!llllMLL £/'/TER/"l/111'411& E..1.U.
)
"-
,_f
flO '" (). '" " ... t .l.'.I .l.'I,
~
t t .. i i t
~ ~J 1 !
.(}17R.
•
l
I'}
CHo»n
/llor1r:-
C'o~.tveR · i91Vt;'LE5 or
TEM PlJ'I T~ tt!?E' /VO T 9o:
\HoRll:.oNT"'L J..JNc_
r- .. ~o.D.EL SE~ ow,,. M-:2..587 t::.o. 458- ?"'Y
I~ B.~S. , I I ~~;i,:»I I 1~~ I 1.-;"::;fn. )(/;AL. ;>zi
MA'TU!t•A'"- I I I C:U\Afl'\t"\AN I I I 60W""f .c\~P .. tWlQ
AIR 5ERV1Ce:j re.MPJ..Are. .r- - , · W11v~ Seer/ON
e,f'.jc.1N£!'~1"G: 01v-. D·D a.v ~<>MAS /"1oRsE -/"18· 3-/"1o,oe-, 1'1-259/ ......,. Plr.tL W~-llP.
FIG. 8
~ )
00
,.. .
:i..Soo---- ------'_J
. 2.2.So-------
2.otNJ----~-~
r------- /. rso "'~
I.Sao----~
I. :Z..54 -----'
1.aoo
~
'I)
"'
~
"'
,-,sol
511 ~~ <:> ~ ~ <:> ~ .., \) \) ~
"'~"'" ~
<> <:> <:> ..,. ~'I\ • .., °' ~ a: ~
2
~
~
~
~
';)
~
'
~
t ...:
.~. ~
<:>
t'(
\) '
~
~ !
'
• ttlll l l l l 111 l
- \ Y°RllVl:J LavveR Eot;IE OF ·7&"'1PJ..AT£1
DovSL.IE S1:z6.
•.
r
H EAT TRl:AT,
FIG. 0
·-r.;..
I~ 61- 2:
TNO/"flf.$ /"?o.RSE /"18-3 .
Secru~/V £:-El -1 /"7- ::Z .s 92 'I'
i ,.;$#'' 2...5de t·.50~ -i
· I I \_I '
FI M 16H
~
-:
\ N
7No"'1,qs MaRse-/"18-3 J SE~'r.-o/Y !!:-E.
/"1·2. .!J 9 2
5 TA/"1 P;-
,Acru11t1- Sn!E
CHECKER APPPOYEO I 00 ... T'.A l"l" ltO'll'l! I)
,,.,..ME '!'\I CC NUHe.a'
~
c
~
[...._~-- ---------------~
r·•1 ~~I8 OU
I F
:Z, .38
I I
I\ I I
I
I -./I l--+--.1+-
I
I
I Frl I I
" · 98
~ E=d I ~ ·- E=x_i I ' f ............. ~
- ......
SCA4E-1..
/fO S/Z~-
T£MPLA7'£ Folif SEcr/o/Y''r.r"'src D'Wt. ,..X-3 9528 ·
T/.fe THt:JM.4$ MORs~ MS·3 W//vO ruNNEL IV/oOE/..
Sre 0 ~:,. /'1-2 5 87-
FIG. 10
~
=-
'OrrJl'VCEN 4-"9
Al~ SERVICE:
£-MGltlEHtiN6 blPT
'1Cl:OOK' .•1£lD ·
/""IAXE , R'-'DD~R
25 - - -- -·
~"
ri
1-.3
W //vD TvNNEL /'4oDEL oF Rtv1 s~o
rA/L s. v.111F"AC£S ON TJ.t'c~AS /"'ft:>~SE Ix~ 3 9 52 7
1"18 - ~
I-'
0
0'"" "' 0" ''
'"°'' I
."..".
I
I
'""'
~ ,-~
i--- -------t'.414 -------..;
1----- ------e. Z'1..3 I
lo--- ---- --Z./ 7.3 I
,__------17~/ I
----- --/. 700 -------.-1
U·M l'
i-----IZ07 '
~ " ~ "I)
~ !!) ~
() ~
.... "':' .... ~ ~ .. "l
" "' "" (I
.. [\J
...... (I (I
' ...;
(I () 0
~~ ~ .
" ~ ~ \I) '
,011e:
w
~-- 42. _I I · /o l I T h
TJYt:J.H/?~ Ho.r~e H~-:.3
I. 5T.411/UZ.e,e 4. t:L l!"VAT02 ·e-.e-n.:>et:J r .5~cr 10N r-r x-\.S'l5<:8 ~
I z •.·. -"'-·1 • ,, ,._. .,,,.,,,~, \ • ,· .. .-,.I oz~
J_ 0 Ci I ~· 0 _1
l\i L
.rz~ I , I
...Jms1i:. 1zelf:
\
~ T/10#1195 #IOI?./ L- M tJ-.3
~ ?! cL ,;.Vl'170~ .e-.ev1.r.e"
se-~rtoN rr x- .~'15'1:8
rf/U. ..5/ZC-
~Tt9MP
~lll l l l j l l l l l l l ~<o.v~2 Co~~ OF Teww~
... . <:l-l\11>- ~ N ~
PoGltU.~ ~/Zt:-
VA<-INP
GClT T / N Q.CN 409
n8 .. .s ..n c; ··' --'"' -.zz
,Jr~£'-
M'11TE~$\...
AIR ScR.v1ce 11.::."'M P.C A'r.c- roR ..>r,,;B1t.1.?cc 4
Et-1(.INl!.U:t r«o O\v ICi:.£11'7'7'"04'"{.C.eV'.o:ql ...5.<c. r !'=U'r'tJ/l'/t?J
.ff''7.K'.J£ /l'ILJ-J
FIG . 11
~335Z76
I-'
I-'
12
}'
13
Figures 1, 2, and 3 are photographs of the actual air-1
plane.
Figure 4 is a three-view of the wind tunnel model.
Figures 5, 6, 7, and 8 are drawings of wing section&
at different points.
Figure 9 is a drawing of the section of the origina\
horizontal tail surfaces.
Figure 10 is a three-view drawing of the new tail
surfaces.
Figure 11 is a drawing of a section of the new hori­zontal
tail surface.
Figure 12 is a drawing of the Ys size model of the
fuselage.
PROCEDURE
The MB- 3 model was tested in the 4-foot wind tun­nel
at Massachusetts Institute of Technology in the
usual way at 30 miles per hour. The upper wing and
the wing cellule were tested separately.
The fuselage Ys scale model was tested in the McCook
Field 5-foot wind tunnel. The balance spindle was
fastened to the side of the fuselage and the lift taken
on the cross wind arm. The drag was taken on a ·wire
which passed out through the honeycomb to a set of
Toledo scales.. Spindle effect was determined by use
of dummy spindle.
RESULTS
Tables I to IV and Figures 13. to 15: L, D, L/D, and
Mc.g. for the original model.
Tables V to VIIl and Figures 16 to 18: L, D, L/D,
and Mc.g. for the original model; with new tail plane.
Tables IX to XII and Figures 19 to 21: L, D, L/D,
and Mc.g. for revised model; fuselage lengthened 173'
feet; with new tail plane.
Tables XIII to XVI and Figures 22 to 24: L, D, L/D,
and Mc.g. for revised model; fuselage lengthened
2 feet; with new tail plane.
.Table XVII and Figures 25 and 26: L, D, L/D, and
Mc.g. for biplane cellule.
Table XVIII and Figure 27: Le, De, L/D, and center
of pressure for upper wing alone.
Table XIX and Figure 28: Yawing moments original
length fuselage, fu selage lengthened 173' feet and
fuselage lengthened 2 feet with new tail.
Table XX and Figure 29: L, D, and De onYs size model
fuselage with landing gear and pilot.
TABLE I
Name of model: MB-3 (original model) .
Wind velocity : 30 miles per hour .
Authority: Massachusetts Institute of T ech nology .
Scale model: 1/16.
Date of test: May, 1922.
L D L /D x
- ----- - ------ - -
-8 - - - - - - - - -- -- - - - - - -- - - -- - - - - - - -
-6 - - - - - - - - -- - - - - - - - -- -
- 4 - - - ----- - - ---- - --- -- -
-2 -0. 234 0.1901 - 1.23 0.199
0 . 042 . 1752 . 24 _ 175
+2 . 314 .1722 1.83 . 161
4 . 593 . 1808 3. 28 .140
6 . 860 .1987 4. 33 .108
8 ' J. 095 . 2269 4. 82 .072
JO 1. 346 . 2595 5. 18 .022
12 1. 617 . 2982 5. 42 -.044
14 1. 870 . 3492 5. 36 -.114
16 2. 085 . 4081 5. ll -.183
18 2. 185 . 5106 4. 28 -.189
20 2.181 . 6667 3. 27 -.123
22 2. 146 . 8133 2. 64 - .051
i equals angle between thrust line and wind .
Angle of stabilizer chord to thrust line, 0°.
Angle of elevator to stabilizer chord, 30° up.
z .
- --
- - -- - ---- -
- - - - - -- - - -
- 0. 228
. 042
. 320
. 605
. 876
1. 118
1. 372
1.644
1.900
2.118
2. 235
2. 277
2. 295
- - ---
- -- - -- -- -
- -- - - -- - -
l. 450
J. 434
1. 531
1. 618
1. 727
1. 874
1.982
1. 896
1.662
1. 456
1. 226
1.105
. 561
TABLE II
Name of model: MB- 3 (original model).
Wind velocity : 30 miles per hour.
Authority: Massachusetts Institute of Technology.
Scale model: 1/16.
Date of test: May, 1922.
i L D L /D x
--- --------- --
-8 ------ ---- ---- - --- - - ----- - --- - ------- - - -
- 6 1:::::::::: - --- ------ ----- - - - - - - - --- - - - - -
-4
-2 -0. 090 0. 1236 - 0. 73 0.121
0 .188 .1129 1. 67 . 113
+2 . 467 . 1155 4. 04 . 100
4 . 754 .1276 5. 91 .075
6 1.026 . 1492 6.88 . 040
8 1.312 .1828 7. 17 - .002
10 1.581 . 2213 7. 15 - . 056
12 1.848 . 2717 6. 80 - . 112
14 2. 097 . 3343 6. 28 - . 186
16 2. 323 . 4036 5. 74 - . 255
18 2. 447 . 5005 4. 89
I
- . 279
20 2. 458 . 6911 3. 56 - .192
22 2. 433 . 8519 2.86 - . 123
i equals angle between thrust line and wind.
Angle of stabilizer chord to thrust line , 0°.
Angle _of elevator to stabilizer chord, 0°.
TABLE III
Name o[ model: MB-3 (original model).
Wind velocity: 30 miles per hour.
z
- -------- -
--- - - - --- -
-0. 095
.188
.471
. 762
1.036
1.326
1. 596
l. 864
2. 115
I
2. 343
2. 475
2. 547
2. 577
Authority: Massachusetts Institute of Technology.
Scale model: 1) 16. ·
Date of test: May, 1922.
11c. g.
- - - - -- - - -
- - - -- - - --
-0. 061
+. 017
+.Oll
+. Oll
- .031
-.054
-. 094
-. 140
-. 253
-. 293
- .64Q
-. !89
- 1. 215
I
I _i - L \ · D I L/D X I Z M o- g I
-=;- ~===I== ~I====-- -6 --- -- ---- _______ ___ ! _____ _____ __________ 1 _________ --- -
- 4 - - - - -- -- - - ------ -- - -'--- - - ----- --- --- ---- -- - ------- --
- 2 0. 100 0. 1876 0. 53 0. 192 0. 094 - 1. 982
0 . 356 . 1668 - 2. 14 . 167 . 356 - 1. 789
+2 . 633 .1741 . 3. 64 .152 . 610 -1. 122
4 . 903 . 1.885 4. 79 . 125 . 915 -1. 652
6 1. 164 . 2136 5. 45 . 092 I. 1 2 - 1. 527
8 I. 412 . 2448 5. 77 . 0<.6 L 432 - 1. 44J
ig u;~ :m~ 1 ~J~ =:&<i~ ::~~~ =u~~
14 2. 154 . 4001 ' 5. 39· - . 135 2. 187 - 1. 436
16 2.378 .4732 5.03 - .201 2 418 - 1.527
18 2.517 . 5809 4. 33 - .225 2.577 -1.679
20 2. 512 . 7556 3. 32· - . 150 2. 619 - 1. 923
22 2. 483 . 9005 2. 76 -. 096 2. 641 - 2. 085
i equals angle between thrust line and wind.
Angle of stabilizer chord to thrust line, 0° .
Angle of elevator to stabilizer chord, 30° down.
T~BLE IV
Name o[ model : MB-3 (original model).
Wind velocity: 30 miles per hour.
Authority: Massachusetts Institut~ of Technology.
Scale model: 1/16.
Date of test: May, 1922.
I :rvro:rllents about c. g. with various elevntor settings I ' +™'°'"I +" +w' _,w I -" I ,;;,~
I I
=-~~ - J _____ ::::::::::::: ::::::::::,::::::_: __ ! ______ __ _
--- - - - - - --- - - - __ _ _ _____ ___ . _ _____ ! _ _______ __ --------
1.450 . I ' I -1.932
I
0 1. 434 -- -- - --- - - -- --- --- --!- - - -------.------ - - - - -1. 739
I +:, u~ ::-~~~~~~~ ~~~~~~~::::=~:-:=::::·:::===::::i =t m.
8 1.874 -- -- - --- -- ----------!----------:- ~1.419 i& i: ~g~ :::::::::: ::---- ----i--::::::::1:::::::::: =): ~~~
14 1.662 _____ __ ___ __ __ -: ___ - ----, - - ___ __ __ I - 1.436
16 1. 456 --- - - - ---- --- --- - -- -1. 527
~g i:i~~ ---.------- ----------:----- -- --- --- - =U~~
24 . 561 ===== == === ===== -====
1
====
1
I -2. OS5
i equals angle between thrust line and wind.
Angle of stabilizer chord to thrust line, 0°.
Angle between wing chord an'.l t hrust line, upper, root, + 3°; loRer
root, - 40'; tip, upper and lower, -40'.
TABLE v
Name of model: MB-3 (original model with new tail plane).
Wind velocity: 30 miles per hour.
Authority: Massachusetts Institute of Technology.
Scale model: 1/16.
Date of test: September, 1922.
i L I D I L/D I x z M , .•.
--=;- ==1==~~-==- -----~
:1 ~,'J!!(":li; i ~f ~ : ":~ jfil :~
4 . 705 1 . 1502 1 4. 70 . 101 . 714 1. 218
6 . 976 . 1715 .5. 69 . 069 . 989 1. 238
8 l. 262 . 2011 6. 28 . 024 I. 278 1. 232
lO J. 527 1 . 2375 6. 4~ -. 030 I. 544 l. 2go
12 I. 783 . 2846 6. 2, -. 094 1. 802 1.150 ii ~:g,:? 1 . :~1~ u~ =: ~~~ ~:g~~ ~ ~i
18 2.314 1 . 5302 4.37 -. 2!0 2. 364 1 .707
20 2. 336 . 6861 3. 40 - . 156 2. 433 . 390
24 --- - ---- -- --- ------,-- -- --- ·-·1·· ----- -- - -- -- ··· -· · ---- -- -- -
i equals angle between thrust line and winrl.
Angle of stabilizer chord to thrust line, + )1°.
Angle of elevator to stabilizer chord, 20° up.
14
TABLE VI
Name of mode!: MB-3 (original model with new tai l plane).
Wind velocity: 3C miles per hour.
Au thority: Massachusetts Institute of Technology.
Scale model: 1/16.
Date of test: September, 1922.
1-i I I
L D L/D x z Mc.g.
---- ---- ----- - - -
!
I
I
I
- 8 ---------- - --- -- ---- ---- - ----- ---- - ---- -
-6 -- --- - ---- --------- - --- --- ---- --- -- ---- -
- 4 ----- ---- - ----- - --- - ---- --- -- ---- -
-2 + o. 069 0.1379 0. 50 0.141
0 . 359 .1326 2. 71 . 133
+z . 654 .1407 4.65 .119
4 . 931 .1583 5. 89 . 095
6 1. 211 .1856 6. 52 . 058
8 I. 481 . 2217 6. 68 . 014
10 I. 752 . 2669 6. 56 -. 042
12 · 2. 014 . 3189 6. 31 - .108
14 2.2'"8 . 3842 5. 89 -. 177
16 2.462 .4550 5. 41 -.240
18 2. 575 . 5989 4. 30 - .225
20 2. 597 . 7527 3. 45 -.183
21 ---------- ---- - ---- ---- -- --- - ---- --- ---
i equals angle between thrust line and wind.
Angle of stabilizer chord to thrust line. + )1° .
Angle of elevator to stabil izer chord, 20° down.
l'J !J- .J ( OlfltillYAI.)
.L.trT & .l/o CllRVe.s'{;:::;.I
4elfo. L."18. ' 11.IT.
P/ir.e : / '?/fY / f'ZZ
/'?OPE/. size ' 0'6 SCALE
WllYP S~&EP : 30 l'lP.H.
S T /16/L /JE/? : 0 °To T.L.
-- ---- --- - ---- -- --
---- - ---- - --- -- --- -
--- -- ---- - ---- - - - - -
0. 064 - 0. 137
. 359 -.975
. 659 -.961
. 940 -.886
1. 224 -. 863
I. 498 -. 814
I. 772 - .803
2. 034 -.779
2. 286 - . 789
2. 496 -.873
2. 634 - 1. 033
2. 700 - 1. 371
-- -- -- --- -
I - - - - --- -
FIG. 13
,_
.'.- ._,__
p·
-
10-
1,5-
v
/'
15
/"J. fJ- .3 (01?/Gl/Y,fL /'?OPEL)
PR,.t/G CVRVES /'"111( Ei.E//. /l.¥ CLES
/rENo. L,fa. , f"l. l.T.
PRTE : ..SrRT. 2~~19'22.
/'700EL S'/ZE: Y16 SCAJ.E
W /IYO S'.PEfV: Jo /VJ.P.H. - srAB1L1ZER o•ro r. L.
+
FIG. 14
I/ ~ ·~c--..
v "' i
y ' -'r v
"' "' "--
\.
\ I
c---,_
~I--...
" "' " I"
I"\
[\.
\
.,_~ -;- ......
v ~
v #!c.G. Cueve-.3
148-.3 O.e1G1NAL /Vlo oc--L
fluTf/02/ TV /11![ #/4y !9ZZ " WINO .5PLTO .JO NPlf f. '"4 .JctJLe- -....._
5TR(}l l!Zel2' .5r rTJN6 o-JO 7ilRV.5T ltNe- ~~ ~ ., ~, 1 r ·r l'-,. j,, l. ,1 ,l ,,
F IG. 15
TABLE VII
Name of model : MB-3 (original model with new t a il plane) .
Wind velocity: 30 m iles per hour.
Authority: Massachusetts Instit u te of Technology.
Scale model: 1/16.
Date of test: September, 1922.
L D L/D x z
16
TABLE VIII
Name of model: MB-3 (original model with new tail plane)
Wind velocity : 30 miles per hour.
Authorit y : Massachusetts Institute of Technology.
Scale model: 1/16.
Date of t est: September, 1922.
Moments about c. g. with various elevator settings
- -- -------- ·---- - - ---~-- 1 -----1
- 8 +30o I t2go +JOo l - 100 I ~~~
- 6
- 4
- 2
0
+2
4
6
8
IO
12
14
16
18
20
24
- ~ 0:g~f --0:-mr --~g:gr- - - -0:- f~r1- ~0:- ggf ----0:~~~t
. 540 . 1215 4. 45 . 104 . 544 . 157
. 827 . 1353 6. 11 . 077 . 835 . 184
1. 107 . 1601 6. 92 . 044 1. 116 . 187
1. 394 . 1937 7. 20 -. 002 1. 408 .170
1.671 .2348 7.11 -.060 1.688 .154
1. 932 . 2866 6. 74 - . 122 1. 950 . 137
2. 175 . 3481 6. 20 - . 180 2. 190 . 124
2, 402 . 4226 5. 18 -. 258 2. 427 . 034
---~~~~-+--~~~~~-- ----~:-~!--,--~~~~~--!-- ~~~~~-- ---~~~~~
i equals angle between t hrust line and wind.
Angle of stabilizer chord to thrust line, +l/2°.
Angle of elevator to s tabilizer chord, 0°.
-30°
----- --1- --
- 8 ----- -- ------- ----- --- -- ---- - -------- -- ------ --- ---- --- --
- 6
-4
-2
0
+ 2
4
6
8
10
12
14
16
18
20
24
!
~~~~~~~~~~ :::~::~i:: ~~~~~~~~~~[~~~~~=~ :~i::i~i:: ~~~~-=~~~
I : . !m H ::!: ~- ~ i
1
- - - --- - _II 1. 081 --- - -- - --- --------- - -. 789
-- - -- - 1. 002 -- --- -- --- :- -------- - - . 873 :::::::::: · ~gb ::::::::::c::::::: =U~~
-- ---- ---,----- -- -- - ----------,I -------- - ------ --
i equals angle between thrust line and wind .
Angle of st a bilizer ch ord to thrust line, + 1/2°.
Angle between wing chord and thrust line, upper, root, +3°; lower,
root, -40'; tip, upper and lower, -40'.
/'? B - .3 { OR/6/HAL /'?OPEL
WITH IVfWT4/lPlAN£
Ltrr & 1/o CVRYL:S
,?ERO. J./IB · : f'1. /. T.
F IG. 16
DATE : Se.PT: 2'~1'72Z
/t?OPEL SIZ& : 1// 1:. SC,fJ.~
Yv!NO S PEEO : .30 /"?.P.H.
ST'4ll1LIZ.t:'R : ,,...~ • ro r. L.
.S
,...
0
+
0 ---
5
I'-
·IS
- r
-
,17
/'J CJ -.3 {OIU61/V/Jl /'?OPEL
WITH N£W TAIL PJ./IHE
OHAG CvH;'.es- rOK .CLE//. ,7,Y,;u
/T.eKO· LAB· ' /'7. J. T.
PATE 1 sepr. z6//f'2 2
1"7tJOfl SIZE : 1//6 S C;fL/:
WIHO SPEED I JO /'?P.#.
STlfB /.J./ZE.R ; -1-j 0 Tll T.L..
FIG. 17
r-
I"'-
v
'J:
T
" ,-..,
---- ~
r--
!'-..
...- ~ ·-· '
A'c 6 CoRVC-5
. ,,
'\
\
'\ ~-
)t!J:.J CJR/6/N.QL /l?oon .JY1rl/ Ni!w Jim Pu:JN/"'- -
llor;;oRtrY /111 T J e"PT 19.U ~-
hlwtJ .Jn·ro .JOtl?.l"J/. f. '=f' .JcRLr ~ -
.5TRl11uzce .Jrrr11\16 ;-j • J.? mRo.sr LtN.t!'- ~-
Vh r ~ .• r. ,. ) .
FIG. \8
18
TABLE IX
Name of model: MB-3 revi sed ; fuselage lengthened J}-3 feet and new ta il
plane.
Wind velocity: 30 miles per hour.
Authority : M assachusetts Institute of T echnol ogy.
Sca le model: I /16.
Date of test: September 13, 1922.
-;--1--L--l--D-- ~ _ x _ _ __ z __ __ i\_-r_"_""_ · _1
=~ -:::::::::1:::::::::: :::::::::: ­-
4
- 2
0
+ 2
4
6
8
10
12
14
16
18
20
24
-~f HrT0:-im-- -- ~~]r 0
: m -~1- m - ---- n~
. 706 I . 1476 4. 78 . 098 . 713 l. 209
. 979 . 1705 5. 74 . 066 . 992 I. 309
I. 258 . 1977 fi. 37 + . 021 l. 270 l. 273
1. 518 .2335 6. 51 - .033 \. 531 1. 241
I. 785 . 2814 6. 35 - . 097 I. 800 I. 161
2. 036 . 3391 6. Ol - . 163 2. 054 I. 082
2. 262 . 4072 5. 56 - . 232 2. 292 . 994.
~: ~~~--l ___ : ~g~-- __ J_~~-- --~~'.~~--1---~: :~g ______ :~~~
; e'lUals angle between thrust l in e and wind.
Angle of st abilizer ch ord to thrust line, + 1/2° .
Angle or elevator chord to stabilizer, 20° up.
TABLE x I
Name of model: M B-3 revised ; fuselage len gthened l }-3 feet auci new t a il .
plane.
Wmd velocity 30 miles per hour Authority· M
1
as
11
s
6
achusetts Insti t ute of T echnology I
Scale model
Date of test . September 12, 1922
' L D I L/D X Z I M o g I
--- ---- -------- - --- ---- ----,
-8 ---- --- --- ----- -- -- -- -- ------ ------ ----
- 6 ---- --- --- ----- - -- - -- --- -----
-4 - ----- - -- ---------- --- -- -----
- 2 - 0. 063 0.1239 -0. 51 0. 122
0 + . 222 . 1136 1. 95 . 114
+ 2 . 507 .1170 4. 33 . 099
4 . 786 .1300 6. 05 . 075
6 1. 067 . 1529 6. 98 . 041
8 I. 343 . 1874 7. 17 - . 001
JO I. 61 I . 2253 7. 16 - .058
12 I. 859 . 27."13 6. 75 -.114
14 2. 097 . 3390 6.19 - .180
16 2. 324 . 4056 5. 73 - . 250
18 2. 430 . 5271 4. 62 - . 249
20 2. 454 . 6982 3. 52 - 184
24 ---------- ----- - -- -- -- - - ------
i e :.iua.ls angle between line thrust and wind.
Angle of st abilizer chord to thrust line, + 1/2°.
Angle of elevator chord t o st a bilizer, 0°.
------ ---- ---- --- --
--- ---- - -- ---- - ----
-- ------ -- ---- - ----
- 0. 067 0. 051
+ . 222 . 092
. 511 . 121
. 791 . 166
I. 076 . 159
I. 356 . 136
I. 615 .11
I. 858 . 093
2. 118 . 079
2. 352 061
2. 473 -. 217
2. 549 -. 553
----- ----- ----
TABl.E XI
N a.1ne of model: l\lIB-3 rev ised; fuselage lengthened H":i' fee t. and new
ta il plane.
Wind velocity : 30 miles per 'hour.
Authori ty: Massachusetts Institu te of T echnology .
Scn le M odel: 1/16.
Date of T est: September 13, 1924.
L D L/D x z f1 ~'~gl ,::~T~iri ':u '~ ~t:~ ~ 1:Yn ;~~i 1 ~: ~g :8~~ 1:m =i:6~~
8 I. 454 . 2210 6. 58 +. 016 I. 471 -. £65
10 l. 717 . 2629 6. 53 042 I. 738 - . 957
12 1. 962 . :n27 6. 28 102 1. 985 -. 957
14 2.214 .3781 5.85 169 2. 238 - .996
16 2.436 .4517 5. 30 236 2.46.5 -1.064
18 1 2 540 . 5714 ·4. 44 231 2.592 - 1. 276
~~ - --~-~'.'-- !---~:2~:--1--- ~~~~-- _____ '.~~-- ___ :_~~~-- --~ ~~~:~
i pqun ls a.ogle bet.w een thrust line nnd wind.
Angle of sta bli zcr ch ord to thrust line, + 1/2°.
.\ nglc of ele vator chord to stablizer, 20° down.
TABLE XII
Na.me or model: 1\IIB -3 re vised; fu selage Jcngth cnccl 17'3 feet. a.nd new
La il pla ne.
\nnd velocity : 30 miles per hour.
Aut hority: M assachusetts I nst itute of T echnology.
Scale mociel: 1/16.
Date of test: September, 1922.
------- -------
lVf omeots a.bout c. g. with various elevator settings
i
+ 30° I +zo0 np + 10° - 10° -20°clown -30°
=~ ::::::::::!:::: ::::::::::::: _:::::: ::::::::::: :::::::: - 4 _____ _____ I ___ _
- 2 I. 0(;4 - \. 065
0 I. 136 - 1. 123
+ 2 I. 221 - 1.120
4 I. 269 - 1.121
6 I. 309 - 1. 039
8 I. 273 - -------- - - - ----- - - - - . 965
10 I. 241 --- -- ---- - - --- - ----- - . 957
12 1.161 ---------- -- -------- - . 957
14 \. 082 -- - - -- ---- ------- --- - . 996
16 . 994 -------- -- --- ---- --- - 1. 064
18 . 701 ----- ----- ---------- - 1. 276
20 . 394 1------------ - ------ ­-
1. 648
24 -- --- - - - -- -------- - - i-- -------- - ·-- --- ------------- - ----- - --
i equals angle between Lhrust line and wind.
Angle of sta bilizer chord to thrust line, + 1/2°.
Angle bet\veen wing ch.Ord and thrust line, upper, root, + 3°; lower,
root, - 40'i tip, upper and lower, -40' .
19
f'1 B- ~ lfEw.rrP-/'VJrl.Atfr LENtiTHrNr
/ j TT. 6 NrW TAIJ. Pi,fKr
LIFT & l./,o CV/i'n:s
/lr/rO L,f4 : M .. /_ T.
'7Arr , srn: Z7, lf'z.
/'70QL:i SIZE : 1/11. SCALE
\'VIND ~PL:£D ' .!JO r?.Plf.
sr..111111..1ZER : 4- ' • T• r. L.
FIG. 19
n 13 _ 3 H~n.sro (Fp.rrLA&z LL'N&THrNrP IJ'r. - l& NZW TAIJ. PL;f/YE
01(,ft; CVHVfj l'IJR E LEI'- A/f'tiLrs
/f,Ftr(). JJf/f. ' 1'1. 1. T.
bATe : SPPT. Z ~ IJ'.L Z
/r;IJD,eL 312 £ : 0'6 SCALE
WINO SPEED :.30 ~,P.H.
STA61.t1ZFR r+j-•ro 'T.L .
F IG. 20
20
/'"1--+-+-+-+-!--l--J--j--ji--i--l-l-+-+-+-+-+-+--+--+--+--+-+-+-+-+--l
\
•:: .. 0
\
L .
:..... ......-- 7/ •Lor N
#.t.6. Cv.eYe.> ~'-..,....~~~~--<
..,.+-+-+--+--+--+--+--+-->--1"J:r~0~:;~~T. ~::/. ,{:}etn6L" UK6;~e;:o
t-+-+-+-+-+--+--+--t--t---lfY11VO./PLL-O .JoJJ'l.Pll li.-:;'..:C,qt.e ~ .
t-+-+-,+i-+-!--l--l~l--1-l./TRlltU zJ;',r_..Prrr1Nti•J • 70 J;,.ev~TL!Ne
:.
'!'ABLE XIII
Name of model: MB-3 revised; fuselage lengthened 2 feet and new
tail plane. ·
Wind velocity: 30 miles per hour.
Authority: Massachusetts Institute of T echnology
Scale model: 1/16.
Date of test : September, 1922.
- 8
- 6
-4
- 2
0
+ 2
4
6
8
10
12
14
16
18
20
24
L D L/D z
- :..:ii~ i :i7- - -- ii~i5i:i - - --:..:ii:9ii-- ---ii: i47-- -:..:ii.-i4:i-- ---- i:i83
. 142 . 1398 I. 02 . 140 + . 142 ]. 255
. 426 . 1409 3. 02 . 12i . 432 1. 369
. 711 . 1510 4. 70 . IOI . 720 I. 427
. 997 . 1730 5. 76 . 066 I. 010 I. 429
I. 272 . 2002 6. 35 . 022 l. 292 I. 403
1. 552 .2378 6. 52 - .038 1.592 l.362
I. 818 . 2879 6. 31 - . 098 I. 840 ]. 261
2. 055 . 3429 6.00 -'-: 168 2.072 1.1 74
2. 272 . 4104 5. 53 ·- ! 231 2. 292 1 ]. 174
2. 377 . 5523 4. 31 -. 210 2. 433 . 797
2.380 .6848 3. 48 . -.171 2.472 .375 1---------- ---------- ---------; _: ________ ---------- ---
i equals angle between t hrust line and wind .
Angle of stabilizer chord to thrust line, + 1/2°
Angle of elevator chord to stabilizer, 20° up.
TABLE XIV
Name of model: MB-3 revised; fuselage lengthened 2 feet and new tai l
plane.
Wind velocity : 30 miles per bour.
Authority: Massachusetts Institute of T echnology
Scale model: 1/ 16.
Date of test: Septemb er 21, 1922.
_ · _J __ L __ --D--~ __ x ____ z_ _ M , .• .
- 8 ---------- -- --- - ---- - -------- - -- -- --- --- - - --- - ---- - --------
- 6 ------- -- - - - - - ---- -- -- - ----- -- - - - - - - -- -- - ------ - -- -- -- - -- - -
- 4 ------- - -- - ----- --- - -- - - ---- - - ----- - ---- ------- - -- ---- - -- --
- 2 - 0.047 0.1265 -0.37 0.125 - 0. 053 0.056
0 + . 239 . 1169 2. 04 . 117 + . 239 . 106
i + 2 . 522 .1215 4. 30' . 104 . 527 .157
4 . 813 . 1344 6. 05 . 078 . 822 . 180
6 I. 092 . 1598 6. 84 . 044 I. 104 . 163
8 I. 376 v . 1914 7. 18 -. 001 I. 390 . 112
JO I. 647 . 2328 7. 07 - . 058 I. 664 . 102
12 1. 914 . 2831 6.77 - . 120 1.934 .096
J4 2. 158 . 3459 6. 24 - . 18.3 2. 188 . 059
16 2. 388 . 4184 5. 71 - . 261 2. 421 -. 061
18 2.477 .5362 4.63 - .255 2.526 272
20 2. 510 . 6928 3. 62 - . 210 2. 598 003
24 - --- - ----- --- - -- - - ----- - - --- --- - ------ ----- ----- -- - --
·;equals angle between thrust line and wind.
Angle of stabilizer chord to thrust line, + 1/2°
Angle of elevator chord to stabilizer, 0°
/
,..._ .
21
TABLE XV
Name of model: MB-3 rev1,ed; fuselage lengthened 2 feet ·and new
tail plane.
Wind velocity: 30 miles per hour.
Authority: Massachusetts Institute of Technology .
Scale model: 1/16.
Date of test: September 21, 1922.
i L D L/D • x I z
--- ·--- ----- - --- --------1-----1
-8 -------- -- -------- - - - --- ------ ---- ------ ------ -- -- - ----- - --
-6
-4
.,.-2
0
+2
4
6
8
10
12
14
16
18
20
24
-+i:i~048- - --i:i.-i4ii:i-- ----i)~34 -- -- -i:i~i«-- ---i:i.-i:i44-- --:..: i~i:i9i .·
. 336 .1349 2. 49 .140 . 336 -1.135
. 627 .1428 4. 39 . 121 . 633 -1. 119
. 911 . 1600 5. 69 . 096 . 921 - 1. 081
1. 190 . 1874 6. 35 . 060 1. 204 -1. 039
1. 459 . 2211 6. 60 . 014 I. 478 - 1. 004
1. 738 . 2675 6. 50 -. 038 1. 760 - . 988
I. 987 . 3172 6. 27 . ~.102 2. 010 - 1. 027
2.237 . 3827 5.85 -.174 2.265 - 1.015
2. 479 . 4566 5. 21 -. 246 2. 514 -1. 101
2. 588 . 5832 4. 44 -. 246 2. 646 -1. 411
---=~~~~-- ---~'.~~~-- ----~~~~-+~~1=~-- ---=~:~=-- --~~~~~'.
i equals angle between thrust line and wind.
Angle of stabilizer chord to thrust line, +Y.0
•
Angle of elevator chord to stabilizer, 20° down.
TABLE XVI
Name of model: MB-3 revised; fuselage lengthened 2 feet and new
tail plane.
Wind velocity: 30 miles per hour.
Authority: Massachusetts Institute of Technology.
Scale model: 1/16.
D ate of test: September, 1922.
I Moments about c. g. with various elev3tor settings.
I + 30° +20° up +10° \ -10° - 200 -30° _ _ _ _ _ ______ I_ _ _ down ----
=! :::::::::: :::::::::: ::::::::::!:::::::::: :==::::::: :::::::::
-~ 1. ~83 ----------1---------- =l. 1. 55 ----- --- -- ------ -- - - 1.103915
+~ U~~ ::::::::::i:::::::::: =U~i
lg u~ ::::::::::!=::::::::: =JJ~
1124 1I.. 127614 --------------------1-------------------- -- 11.. 002175
!~ 1:::::::::: ---~:-~!L ~~~~~~~~~}==~===~~ -~q~i-r~~:;;;:
i equals angle between thrust line and wind.
11B-.3 REY/SED I rVfEU/6£
,/ENriTHENED .Z FT. 0, /Yelf/ 7/JJL PiA"'
L/rT ~ .Yo culf#'.es
//ER(}. LA8. : ;vJ. I T.
DAT£ : ~l!'PT. Z~/fZZ
/'700.t:'L S/,ZF : W' SCA.LE
W/IYO SPErO :30/"'JP.H.
STALJ/L/.Z.e'l'f _._,.. 1 "'74 T.L .
FIG. 22
.5
~
/
·-
5
0
,......
. s.
I
z •
- .
22
n f3 - .3 /?J'Jl'/SEP z.r:-;:c T~~N'G~~:,-;n z FT.
.0RA6 CV/f/l~.r F "R ELEV AIYCLES
/f£NO. ,/.A11. ' l'1 /.T.
OAT£ : SEPT. 2?;/f'Z2
r?OPEL SIZE ! 0, .St:ALE
W llYO SP.CED "'o n.P.N •
.5TA81Ll.2FI< : .,..L·ro 7':L.
FIG. 23
~ .,,, r--
-..
I"-.
' \
\
( .
!'-..
"
- ['--.
'
/!c.G CoRve~
'\
HIJ-J R~v1.,e-o noo~t- rv,,eLR6~ Le. ~11c.Neo en:
Por11oe1TY t'?.IT. je,..r. t~rz
IV/NO jfl?O .}O<'fl?JI. Ji':l!.JCRLJ:"
~m111t.arg .:Jerr/NV ~ i· To7.vKu-'r ilN~
1~ ~ ,., ...... ~ . 'n
FIG, 24
/
23
TABLE XVII
Name of model: MB-3 Biplane, Cell Alone.
Wind Velocity: 30milesperhour.
Auth ority: Massachusetts Instit ute of Technology.
Scale model: 1/16.
Date of test: March 21, 1923.
L [) L/D x
-8 ------
- 6 - -- - --- - ---- - -- -- ----- ---- ------
-4 - 0. 242 0. 0756 -3. 19 0 . 060
- 2 + .013 . 0570 + . 24 . 058
0 . 277 . 0529 5. 23 .053
+ 2 . 534 . 0595 8. 96 . 041
4 . 779 . 0747 IO. 40 . 020
6 I. 024 . 0991 10. 33 . 010
8 I. 274 . 1302 9. 79 . 048
IO 1. 515 . 1713 8. 84 . 096
12 I. 736 . 2180 7. 96 . 150
14 I. 907 . 2790 6. 82 . 192
16 2. 013 . 3505 5. 74 . 222
18 . 2. 090 . 4620 4. 63 . 219
'iO 2. 090 . 5650 3. 70 . 182
24 2. 010 . 6950 2. 89 .110
i equals an ~le betwaen thru3t line anj :wln I.
/1 fj - .3 B/fl.Y/N,e CEJ.lVJ.
.l../FTJ ,P.l(At;_.4 L/i;> CVRV.J!\S
HEA'O. LH.t:J, :/'?.J.T.
.PHTf :/"JfiK,:z~Z.J
~cP.eJ.. .S,12~ ; ~6 BC/i'LE
WINO .:J,P.E'ED !.fJO /"l.P.#..
-
/
-4
,_
/ /'
/'
/
/
/
I z M c. g.
----
----- -- -- - - ------
- --- - ----- ---------
-0. 246 - 0. 310
+.012 -. 209
. 277 - .120
. 5.35 -.028
. 782 +.060
I. 026 . 151
I. 279 . 218
I. 524 . 250
I. 743 . 259
I. 9l8 . 297
2. 030 . 270
2. 130 . 286
2.150 . 255
2, 125 . 121
~- ,_.,..-; ~· .-·
v .v
./ f''
/
v
t--
I'-
'r--..
["--.
""
/l'lc.ti. Cvli! vr->
'111-~ Oelti/N,QJ. /100ti
- -.....
"
\
I\ .
\ ,J -
orrfit' ;,/
\
\
QM 8TPt. IN .,,,,_ V'-
llU..T. llOli!ITY !'ZIT. t'?RR(,JI lfZJ ,,._.,_,.. ·~ ""'OIJ ..;.1 t:; ,_, ,,..
\
\
\
:~ -,.,_ - ·- l
- - . 'A o\
FIG. 2!i FIG 26
"'
'·
TABLE XVIII
Name of model: MB-3 Upper Wing Alone.
Wind velocity: 30 miles per hour.
Authority: Massachnsetts Institute of Technology.
Scale Model : 1/16.
Date of test: March 21, 1923.
a: ~1 L, I D, C.P.
- 4 -5.01 I -0. 00046 o. 000092 +o.09
-2 -1.62 -. 00009 . 000057
0 6. 71 . 00031 . 000046
2 13. 93 +. 00070 . 000050
4 15. 84 . 00105 . 000066
6 15. 44 . 00140 . 000091
8 14: 20 .00173 . 000122
10 12. 80 . 00205 . 000160
12 11. 53 . 00236 . 000205
14 8. 57 . 00255 . 000297
I
16 7. 14 . 00270 . 000377
18 4. 48 . 00261 . 000583
20 3. 37 . 00251 . 000745
T ABLE XIX
Name of model : MB-3 (revised new tail plane).
Wind velocity: 30 miles per hour.
Authority: Massachusetts Institute of Technology.
Scale model : 1/16.
Date of test: September 27, 1922.
N .; .• . (01'iginal length)
i 30L 20L lOL· lOR 20R
-.52
+.40
. 36
. 32
. 30
. 29
. 28
. 28
. 28
. 29
. 32
. 34
I
30R
----------- ---- -----
0 0. 536 0. 378 0.173 0.158 0. 378 0.542.
12 . 526 . 355 .166 .163 . 352 .490
N 0 . • · (fuselage lengthened 1% feet)
0
I
0. 549
I
o. 385 1-·o. 181 I
0. 185 I 0. 385
I
0.570
12 . 577 .417 .206 . 214 . 397 . 542
. - ·fy ;.!: "<fuselage lengthened 2 feet)
0 I 0. 61 , .. 04~"· 1 -0. 20 I 0. 20
I
0. 43
I
0. 62
12 . 64 .42 .20 .18 .40 .62
I
N •. •. =yawing moments abou t center of gravity Obs. ins.); +71!0 =
angle of stabilizer chord to thrust line.
TABLE xx
Name of model: MB-3 model; fnselage with chassis and pilo~ in
place.
Scale model: J /8.
Authority: McCook field 5-foot wind tunnel.
Date of test: October. 30, 1923.
[Frontal area=0.2576 square feet]
1' v V' D L d I
Deg. m.p. m.p. h. h. lbs. lbs. #/m.p.h. #/m.p.h. ;
----------------
0 'is. 2 5,650 · 'i . 186 0.105 0. 000210 0. 0000186
0 104. 5 10,920 2. 229 . 439 .000204 . 0000401
0 127. 0 16,130 3. 241 . 631 . 000201 . 0000391
0 150. 7 22,700 4. 376 . 778 . 000193 . 0000343
- 4 127. 0 16,130 3. 415 -. 610 . 000211 -. 0000378
0 127. 0 16,130 3. 241 +.631 . 000201 + . 0000391
8 127. 0 16,130 3. 371 3. 406 . 000209 . 000211
16 127. 0 16,130 4. 057 5. 752 . 000252 . 000357
D, #/sq. ft./ I
m. p.h. I
0. 000815
. 000793
. 000782
. 000749
. 000820
. 000782
. 000812
. 000978
24
FIG. 27
-8 . lll"PEK W,N6
l'iA~ACTE~ISTJ< CUil. t"IS.
25
-
.
/'1 i:J - 3 /i'EVl,FEO-NEW7ll/L PL"1M
YAW//Vti /'10/>/ENT CVHJ/£S
/Yi'KO. L/IB. : /"7. /./.
PATE : Ocr. ~ /f'ZZ
.SC:.41.E : 1//6
' W/HO SPEEP : 30 /'2,P.#.
.. S7AB/L/ZFI'? 'jfro r.L.
/YoTE: .L//YE.J" 0/l'/G//¥"11. l.EN<iTH FP.TE,t.At;E ----- ~- r«SE,t. "9tr.E .LENGTH.1'/VED 1-jrr.
- .. ~ .. .:Z FT.
r
l
-
.
FIG. 28
..
n.B. ·J ~Scafe Mode/ 10.sela,te anf Chassr's
· S.Coolc Fi~/J Five Toof Wt~d Tunnel 10/30/a.3
lJc 1's hosed on Tro11ial area of ."CS76u'
~ D 1:
'
;·
'
1
'
.
-
'
'
~
FIG. 29
0