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Wind tunnel test of six horizontal tail surface designs having the U.S.A.-47 airfoil section (Airplane Section report)

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              AT\NG
Auburn University Libraries
llllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllll
N 3 1706 025 85062 4
File D 52.32 / 2 7 McCOOK FIELD REPORT, SERIA.L No. 2468
Vol. VI
<AVIATION)
PUBLISHED BY THE CHIEF OF AIR SERVICE, WASHING TON, D. C.
June 1, 1925 No. 511
WIND TUNNEL TEST OF SIX HORIZONTAL
TAIL SURFACE DESIGNS HAVING THE U.S.A.-47
AIRFOIL SECTION
( AIRPLANE SECTION REPORT )
Engineering Division, Air Service
McCook Field, Dayton, Ohio
January 27, 1925
WASHINGTON
GOVERNMENT PRINTING OFFICE
1925.
Ralph Brown Drauglrn11
LIBRARY ' ·
MAY 3 0 2013
Non·Depoitory
Auburn University
CER'l'IFICA'l'E: By direct ion of t he Secretary of War t he matter contained
herein is published as administrative information and is required for t he proper
transaction of the public business.
(n)
. ~.
WIND TUNNEL TEST OF SIX HORIZO AL TAIL SURFACE
DESIGNS HA YING THE U. S. A.-47 AIRFOIL SECTION
OBJECT
The object of this test was to determine t he effect
of plan form and elevator size on the aerodynamic
characteristics. In addition, the variation of hinge
moment with elevator angle was determined in the case
of one design.
DATE AND PLACE
These tests were run in the McCook Field 5-foot
wind tunnel between August 8, 1923, and Jn!~· 22,
1924.
DESCRIPTION
The six horizontal tails a re of approximately the
same total area and aspect ratio, but have .various
plan forms and proport ions of elevator to stabilizer
area; all cross sections parallel to t he plane symmetry
a re the U. S. A.- 47 airfoil, except t hose at t he center,
the portion cut away making a stub section.
Figure 1.- Plan view of right half of tail surfaces.
The design characteri stics of the abo,·e tail surfaces
are tabulated below:
Per Total cent I Aspect Photo
•rail area Stabi- Ele- ele- of
sur- (A) lizer vator vator Wing section S(psa) n ratSio' total face square area area area of ~ A: draw-inches
total ing
area
·---- - ·---- ----
27. 00 17. 08 9. 92 36. 7 u: S. A.-47 ___ 9 3 Fig.2.
'l:i. 04 16. 78 10. 2fi 39. 2 U .S. A.-47 ___ 9 :l Fig.3.
27. JO I 17. 02 10. 08 39. 8 U.S. A.-47 __ _ ~- 251
2. 99 Fig.4.
27. 07 18. 82 8. 25 30. 5 U. S. A.-47 __ 3. 16 Fig.5.
26. 67 15. 86 10. 81 40. 7 U.S. A.-47 ___ 9. 25 3. 20 Fig. 6.
26.15 12. 95 13. 20 50. 5 U.S. A.-47 __ _ 9. 25 3. 27 Fig. 7.
The U. S. A.-47 airfoil is symmetrical about the
center line and tlie ordinates are ta.ken from the upper
half of the Gottingen 409 section.
TABLE !.- Ordinates of the U. S. A .-47 air.foil section
Per cent
chord
0
1. 25
2. 50
5.00
7. 50
10. 00
15. 00
20.00
30.00
40. 00
50.00
60.00
70. 00
80.00
90.00
95. 00
100.00
I Ordinates in
per cent chord
upper and
lower
0
2.10
2. 85
3. 69
4. 31
4. 85
5. 55
6. 04
6. 47
6. 47
6.15
5. 39
4. 37
3. 23
1. 83
. 95
0
PROCEDURE
The six surfaces were tested in the usual manner and
the elevator was set with respect to the stabilizer by
the use of a graduated template.
In order to accurately measure the elevator hinge
moments on a tail surface, No. 5 was equipped with a
hardened pivot with a screw adjustment in each end
of the elevator hinge, thus eliminating the original
clip hinges and suspending the elevator between the
two hardened points. A small hole was drilled in the
elevator l :li in ches from the hinge line and a small
silk thread tied in the hole, passed vertically through
a 72-inch guard tube to a set of small Toledo scales on
top of the tunnel. The angula~ setting of the elevator
was determined by sighting the cross hair of a telescope
along a scratch on t he end of the elevator.
RESULTS
I. Aerodynamic characteristics:
Surfaces: Nos. 1, 2, 3, 4, 5, and 6.
Stabilizer at 0°.
Elevator at +30° to -30°.
I Figure Graph
8 Lilt: vs. elevator angle.
9 Drag vs. elevator angle.
.10 L ID n. clerntor angle.
ll C. P .. travel \ "S . elevator angle.
!~ M ( L. E .) vs. elevator a ngle . ·
____ !_ ·- ----- -------
These data are tabulated in Tables 2, 3, and 4.
II. Aerodynamic characteristics with various stabilizer
settings:
Surfaces: Nos. 4, 5, and 6.
Elevator at + 30° to - 30°.
IF .i gnre Ssteathtiilnizge :- j 0_ T r~p ". .
__13 _ - + lQ 1
1
Land D vs. elevator angle.
14 +.' Do.
15 o Do.
16 -5 I Do.
17 -10 Do.
18 +IO LID and M vs. elevator angle.
19 +.5 Do.
20 0 Do.
21 - 5 Do.
22 -10 Do.
These data are tabulated in Tables 5 to 13, inclusive.
III. Hinge moments:
Surface: No. 5.
Elevator at +30° to -30°.
Stabilizer at + 10 to - 10°.
See Tables 12, 15, and 16, and Figure 23.
46S93- 25t- l (1)
2
IV. a. Lift vs. Stabilizer setting with elevator free
and at 0°.
b. Neutral angle of elevators vs. Stabilizer setting.
(Elevator free to move about hinge pivots.)
Stabilizer at + 10 to - 10°.
This data is tabulated in Table 17 and plotted in
Figure 24.
REMARKS AND CONCLUSIONS
The above results can not in general be applied
directly to actual airplane design since most airplanes
use much thinner sections for tail surfaces. Moreover,
the aerodynamic characteristics will undoubtedly be
different when used in connection with the rest of the
airplane.
From Figure 8 in comparing the lifts of horizontal
tail surfaces Nos. 1, 2, 3, 11:nd 5, which have about the
same proportion of elevator chord to total chord, the
curves indicate that shapes Nos. 1 and 3 are the better
and Nos. 5 and 2 are about. equal. What happens
when this proportion of chords on Nos. 1, 2, and 3 is
increased is not known, but No. 4 and No. 6 show the
effect of decreasing and increasing this proportion on
No. 5. No. 6 has much the greater lift and No. 5 is
greater than No. 4.
Figure 23 shows that the hinge moment is a linear
fun ction of the elevator angle.
TABLE 2
Name of aerofoil : '!'ail surfaces No. I and No. 2.
Wind velocity: 40 miles per hour.
Authority: McCook Field.
Date of test: August 6, 1923.
Ele-
D I L/D Mr .. E. i vator L
setting
- -- ·--- - ------
NoL!
81 -30 0. 517 0.131 3. 940 ·- 1. 140
-20 . 383 .080 4. 808 - . 899
0 -JO . 261 .034 7. 6\Jl - . 610
0 0 -.007 .012 -.583 +.Oil
0 +10 -. Z/5 .030 -9. 070 . 612
0 +20 -.368 .076 -4. 840 .838
0 +30 - . 511 . 133
0 -20 . 345 .077 4. 464 -. 782
C. P. %
chord
52. 25
55. 57
55. 38
36.93
52. 78
53. 97
53. 90
57. 50 I - 3. 847 1 1. 161
No 'l 0 -10 . 222 . 033 6.770 - . 512 ui:~
0 0 -.033 . 016 -2. ooo I -. 105 114. 90
0 + 10 -.251 . 038 -6. 600 I . 528
1
53. 42
0 +20 -.364 . 084 -4. 312 . 770 53. 75
0 +30 -. 458 . 152 -3. 017 . 992 55. 00
NOTE.-Elevators are considered to be at a positive angle when they
give a positive pitching moment.
TABLE 3
Name of aerofoil : Tail surfaces No. 3 and No. 4.
Wind velocity: 40 miles per hour.
Authority: McCook Field.
Date of test: August-, 1923.
·\ I i vEalteo-r L D L/D
___ --- _setting
--- --- ---
No, l 0 -20 0. 374 0.086 4. 330
0 -IO . 262 .033 7. 855
0 0 - .010 . 014 - .714
0 IO -.277 .038 -7. 200
0 20 -.356 . 085 -4.194
0 30 -.496 . 148 - 3. 355 r -30 . 444 . 106 4.177
---- - - 20 . 299 1 . (){i4 4. 686
-IO . 145 . 031 4. 635
No.4 . 0 -.008 .018 -. 499
+10 - .1 72 1 .032 -5. 380
'20 - . 314 . 063 -4. 960
30 I - .446 • JOO -4. 446
i J\-!L. E. C . P. % 1
chord
- -----
-0. 726 46.80
-.491 45.20
-.066 { 39. 82
67. 42
+.544 47. 27
. 724 49.00
. 996 48. 28
- .622 46. 73
- . 478 53. 33
-.219 50. 33
+.007 27. 36
. 250 48. 46
. 451 47. 86
. 620 46. 36
TABLE 4
Name of aerofoil: Tail surfaces No. 5 and No. 6.
Wind velocity: 40 miles per hour.
Authority: McCook Field.
Da te of test: Augus t 7 and 8, 1923.
Ele- C.P.% i vator L D Lf D M(L.E.) of chord setting
--------,_ ------- -----
No; l 0 - 30 0.480 0. 130 3. 700 -0. 639 44.36
0 -20 . 346 .080 4. 310 - . 472 • 45. 50
0 -JO . 225 . 041 5. 510 -.311 46.13
0 0 .0.12 . 017 . 717 -.021 { 52. 43
95. 66
0 +10 -.221 .035 -6. 320 +.307 46.06
0 20 -.340 . 077 -4. 400 +.455 44. 60
0 30 -.468 . 124 -3. 780 . 608 43. 30
No O l 0 -30 . 527 .168 3.140 - .622 39.36
0 -20 . 391 . 106 3.688 - . 469 40.03
0 - 10 . 305 . 047 6.450 -.348 37. 96
0 0 .013 .020 . 650 + . 006 31. 49
0 10 -.291 . 040 -7. 310 .345 39. 53
0 20 - .373 . 092 -4.064 . 459 41.00
0 30 -.499 .149 -3. 343 . 604 40.36
NOTE.- Elevators are considered to be set a t a positive angle when
they give positive pitching moment.
TABLE 5
Name of aerofoil : Tail surface No. 4.
Wind velocity: 40 miles per hour.
Authority: McCook Field , 5-foot wind tunnel.
Date of test: October 10, 1923.
vEalteo-r 1
angle
K, I K , I Mc(c. •. ) I ca;;· JM(r .. E.)
chord
I
Stabilizer angle, 0°
I
+30 -0. 470 0.105 - !· 4731-0. 001580 o. 000353!+ o. 000740
+20 -.325 . 064 -o. 080 -. 001090 . 000215 +. 000521
+10 - .173 .030 -5. 765 -. 000553 .000101 +. OOOZ/4
0 o · . 014 0 0 . 000047 0
-10 +.152 .030 +5.065 +. 000511 . 000101 -. 000259
- 20 +.3101 . 064 +4. 843 . 001040 . 000215 -.000504
-30 +.4491 . 104 4. 318 . 001510 . 0003501 - . 000714
I
Stabilizer angle -5°
+30 -0. 6901 0. 148 -4. 660 -0.002320 0.000497 +o.000903
+20 -. 555 . 094 -5. 900 -. 001867 . 000316 + : 000699
+10 -.440 . 049 -8. 980 - . 001480 . 000165 +. 000495
0 -.263 . 024 - 10.960 -.000884 . 000081 +.000221
-10 -.082 . 028
1
- 2. 930 -. OOOZ/6 . 000094 -. 000049
-20 +.084 . 045 +I. 867 +. 000282 . 000151 -. 000344
-30 +.231 . 078 +2. 9621 +. 000777 . 000262 - . 000560
i equals angle between chord of wing and wind.
Tail surface No. 4.
Area,'square foot, 0.186.
Elevator chord, 0.965 inch.
Chord, 3.00 inches.
Span (ma.,imum), 9.25 inches.
TABLE 6
Name of aerofoil: Tail surface No. 4.
Wind velocity: 40 miles per hour.
Authority: McCook Field 5-foot wind tunnel.
Date of test: October 10, 1923.
46. 80 0.661
47. 80 . 465
47. 30 +. 245
± OC 3
50.60 - . 231
48. 50 -.450
47. 40 - .638
39.20 0.806
37.00 .624
33.30 .442
24. 80 +. 197
-17. 50 - . 044
128.00 -.307
74.60 -.500
vEalteo-r1 K,
angle
Mc
(L .E.) I
c. P.I % M(L.E.)
chord
Stabilizer angle + 10°
I
+30 -0. 0481 0. 067 - 7.170 -0. 000161 0. 000225 +o.000400
+20 +. 1021 . 043 +2. 372 +. 000343 . 000144 +.000193
+10 +.177 . 027 +6. 560 .000595 . 000091 +. 000093
0 . 4541 . 049 9. 265 . 001525 . 000165 -.000365
- 10 + . 621 . 084 7.390 . 002085 . 000282 - .000634
- 20 +. 723 . 143 5. 055 . 002430 . 000481 -.000819
-30 . 8501 . 195 4. 360 . 002860 . 000655 -. 001032
I
i equals angle between chord of wing and win<l.
T a il surface No. 4.
Area, square foo t, 0.186.
Eleva tor chord, 0.965 inch.
Cbord, 3.00 inches.
Span (maximum) , 9.25 inches.
340.0 0. 357
-53.8 . 172
-15.6 +.083
23. 9 -. 326
30. l -.566
33. I -.i31
35. 3 - . 922
c~
\
(
fl =:17. OtJ sq.IN
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TOTAL ARcR 27.07Cf. SQ.IN.
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TOTAL Al?cR 2G. G70 SQ. IN
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A,. TOTAL A~eA OF STRfJIL/Ze~
B-=a 11 ,, " cLE.VATote.
ALL .5cCTION.5 fJRc USA.-47
FIG. I
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EUVATOl'l AHEA 111.26
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FIG . 7
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FIG, 10
12
t--+--+---+---t--+---+~t--+--+----+---+---+~ TRIL SUl?rflCeS (Hoe)
t--+-+--+--+--+---+-+--+---+---+---+~ ~ DIFFERE:/YT TAIL SURFACcS
OF ALl'108T £~URL TOTAL
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FIG. 11
13
TAIL .SURF"~S (HOR) TRIL.
6 D/rreReNT TAil SVRFfiC'c.5 SU~FRC~
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FIG. 12
14
TABLE 7
Name of aerofoil: Tail surface No. 4.
Wind velocity: 40 miles per hour.
Authority: McCook Field 5-foot wind tunnel.
Date of test: October 10, 1923. L D
TABLE 9-Continued
L/D Mc
(L.E.)
EleC.
P.
vator
a ogle
3 ML.E.
chord
E
le- 1
I I I I v a tor L D L/D K, K, IM c(L.E.) I C3. P. I ML.E.
an gle chord
'
Stabilizer angle, -10°
HO -o. Bl?4lo. 211\ -4. 190 -o. 00'.2".J70lo. 000109 +o. 001050! 35. 30 o. 936
+20 - . 7o3 . 140 -5. 380 -. 002030 . 000471 +. 000846 32.90 . 755
+10 -. 643 . 0861 -7. 480 - . 002!60 . 000289 +. 00062~ 28. 70 . 559
0 -. 468 . 0501 -9. 360 -. 001073 . 000168 . 000360, 23. 10 . 326
-10 -. 223 . 034 - 6. 855 - . 000784 . 000114 -. 000012, -1. 56 -.011
-20 - . 125 . 047 -2. 660 - . 000420 . 000158 -. 000189 -49. 00 - . 169
- 301 +. 022 . 070 +. 3141 +. 000074 . 0002351 -. 0003681 122. 00 -. 329
Stabilizer angle, + 5°
+ 30 -0. 252
1
0. 081 -3. llOi-0. 00084710. 0002721+0. 000568 69. 51+0.' 507
+20 - . 103 . 045 -2. 290 -. 0003461 . 000151 +. 000342 105. 0 +. 305
+ 10 +. 053 . 025 +2. 120 +. 000118 . 000084 +. 000099 -54. 2 +. 088
0 +. 268 . 024 + ll. 160 +. 000901 . 000081 - . 000254 28. 01 -· 227
-10 +.460 .048 +9.58{_ll +.0015501 . 0001611 -.000550 35. 4 -. 491
-20 +. 607 . 098 +6. 190 . 002040 . 000329 - . 0008ll 39. 3 - . 724
-30 +. 688 . 146 4. 7121 . 002310 . 0004911 -. 000938 39. 9 -. 835
i equals angle between chord of wing and wind .
Tail surface No. 4.
!\rea, square foot, 0.186.
Elevator chord, 0.965 incb.
Chord, 3.00 inches.
Span (maxcimum), 9.25 inches.
TABLE 8
Name of aerofoil: T a il surface No. 5.
Wind velocity: 40 miles per hoar
Authority: McCook Field 5-foot wind tunnel.
Date of test: October 15, 1923.
Ea tloe-r 1
ngle
v
a
L
I
D
I L/DI I I I I C.P.
K, K, [Mc(L.E.) 3 ML.E
I
chord
Stabilizer a ngle. 0°
+w _, ..,1 " •+• ~L, "''[" ""'" H ..,,.
42. 9 0.620
+20 - . 3441 . 073 -4. 710 - . 001180 . 000250 +. 000512 43. 5 . 449
+rn - . 243 .034-7. 04ol -.ooo830 . 000118 +.000340 40.8 . 298
0 +. 005 . 016 +. 3031 +. 000020 . 000056' - . 000040 231. 0 -. 035
- 10 +. 209 . 039 + 5. 2901 +. 000720 . 000135 - . 000337 47.1 -. 296 -:io +. 343 . 081 + 4.2421 + . 001!40 . 000277 -. 000542 46. 0 -.476
-301 . 460 . 124 +3. 6931 +. 0010801 . 0004261 -. 000715 45. 4 -.62ll
i equals angle between chord of wing and wind.
Tail surface No. 5.
Arca, square foot, 0.1825.
Elevator chord, 1.285 inches.
Chord, 3.00 inches.
Span (maximum), 9.25 inches.
TABLE 9
Name of aerofoil: Tail surface No. 5.
Wind velocity: 40 miles per hour.
Authority: McCook Field 5-foot wind tunnel.
Date of t est: October 15, 1923.
I
Ele-1
I
va- C. P. tor L D L/D K, K, M c 3 ML.E. 1 (L.E.) chord
a nglel
-- --- ---
Stabilizer angle, +5°
- ·--~- -- - -·
+ :01-::_o. ~111 ~- tJ?l I - 3. 027 - 0. OOO<J50 0. OOO:Jl3 +o. 0005,;g flO. 80
+ 20 -. 148 . 054 -2. 716 - . 000510 . 000187 . 000:!71 75. r>«1
+ IO -. 044: . 0241 -l. 7J - . 0001501 . 0000841 +. 000190 ltiU. 2
0 +. 260 .0251+10.200 +. 000890 .0000871 -.00U24fl 27.[>U
-o: IO +. 51\11 . 063 +8. 237! . 0017801 . 0002_Hi -. 000598 :33.f>
~ 20 . +,_ 620:_ -127, +4. 880_ .-002120 . 000430 - . 000805 37-. 3 ..
- 30 +. 699 . 176 3. 960 . 002400 . 000605 - . 000943 38. 7
I . I _ , _ ___ · __ _
·-
0. 489
. 320
~:m / -.525
- . 706
- .827
Stabilizer-angle, +10°
+30 -o.095 0.077 -1.225 -0. 000330 0.000265 +0.000435
+20 +.036 . 046 +.783 +. 000120 . 000158 +.000238
+10 +.158 . 025 +6.195 +.000540 . 000087 +. 000066
0 + . 450 . 050 +9. 000 . 001540 . 000171 -. 000364
-10 +.663 . 101 +6. 565 . 002270 . 000346 -. 000670
- 20 +.761 . 161 +4. 710 .002610 . 000553 - . 0008691
-30 +.873 . 227 + 3. 838 . 002990 . 000780 -. 001071
i equals angle between chord of wing and wind.
Tail surface No. 5.
Area, square foot, 0.1825.
Elevator chord, 1.285 inches.
Chord, 3 inches.
Span (maximum), 9.25 inches.
TABLE 10
Name of aerofoil: T ail surface No. 5.
Wind v elocity: 40 miles per hour.
Authority: McCook Field 5-foot wind tunnel.
Date of test: October 15, 1923.
Ele- I I
va- L D L/D I K, K, Mc
tor
I
(L.E.)
angle I
Stabilizer angle, -5°
+30 -0. 713 0. 1681 -4. 230 -0. 002440 0. 000577 +0.000925
+20 -. 575 . 1111 -5. 730 -. 002180 . 000380 +. 000778
+ 10 -.498 . 0541 -9. 225 -. 001700 . 000185 +. 000553
0 -.246 . 024 -10. 040 -. 000840 . 000084 +. 000188
-10 -.036 . 027 -1. 333 -. 000123 . 000092 - . 000153
-20 +.150 . 061 +2.458 +. 000510 . 000209 -. 000411
-30 +.264 . 0951 +2. 780 . 000900 . 000325 - .000572
Stabilizer angle, -10°
+158.8
-169. 6
-12.0
+23.6
29.1
32. 6
34. 8
C.P.
3
chord
37.3
35.3
32.2
22.2
-118.06
84.0
65.5
+301 -. 888 0. 221 -4. 010 0. 003040 o. 0001581 +o. 001035. 33. ii + 20 -. 760 .147 -5. 150 . 002600 . 0005051 +. 000836 31. 5
+10 -. 654 .091 -7.190 . 002240 . 000312 +. 000616 27. 3
0 -.452 . 049 -9. 225 . 001550 . 000168, +. 000346 22. 31
-10 -.140 .027 -5.185 . 000480 . 000092 -. 000121 -25. 0
-20 -.040 .053 -. 755 . 000140 . 000182, - . 000272 -165. 5
-30 +.080 . 080 +1.000 . 000270 . 000270, - . 000433 + 197. 5
I
i equals angle between chord of wing and wind.
rl'ail surface No. 5.
Area, square foot, 0.1825.
Elevator chord, 1.285 incheo.
Chord, 3 inches.
Span (maximum), 9.20 inches.
TABLE 11
Name of aerofoil: T a il surface No. 6.
Wind velocity: 40 miles per hour.
.\uthority: McCook Field 5-foot wind tunnel
Date of t est: October JG, 1923.
0. 382
. 209
. 057
- . 319
-.587
-. 762
-.940
ML.E.
0. 811
.682
. 458
+.165
-.135
- .361
- .502
0. 908
. 733
.540
. 303
- .106
- . 239
-. 380
vEatloer- 1
angle
L Ky Mc
(L. E.) I
C. P. ,
3 ML"' ·
chord
Stabil izer angle, 0°
+30\- 0. 5201 o. 1501 1
-3. 33 -o. 00180 \o. 000540 o. 000117 38. 5 o. 622
+201 - . 382 . 092 -4.15 -. 00132 . 000318 . 000527 41. 3 . 457
+10 - .311 .042-7.40 -.0010761 .000145 .000399 37.0 .346
oj -. 001 . 019 -. 0525 -. 000003 . 000066 -. 000024 - 697. o -. 021
-10 . 3041 . 0491+6. 205 + . 001052' . ll00170 - . 000441 41. 9 -. 382
-20 . 3651 . OYG 3. 800 . 00l26:l . 0003:12 - . 0005.;6 43. 9 -. 481
- 30 . 4!!5 . 15fi 3.1\1:3 . 0017~~ . 000537 - . (l(J0725 42. 2 - . f\28
i equals angle between chord of wing and wind.
11ail surface, No. fi.
Area , square root, 0.1805 ..
Elevator chord, 1.r.flO inches.
Chord, 3 inches.
Span (maximum), 9.25 inches .
15
TABLE 12
Name of aerofoil : 'rail surface No. 6.
Wind velocity: 40 miles per hour.
Authority: McCook Field 5-foot wind tunnel.
Date of test: October 16, 1923.
Ea tloe-r 1
ngle
v
a
L
I
D
I L/D I I I
K, K, Mc IC. P . I (L. E.) 3 ML.E.
chord
Stabilizer a ngle, +5°
I
+301-0.340 0. 124 1- ?· 74 -0. 001176 0. 000430 +0.000581 51.1 0. 504
+201 -.218 . 0685 -3. 18 -. 00075 . 000237 . 000409 56.1 . 355
+10 - . 091 . 025 -3. 64 -. 000315 . 0000865 +. 000224 72.8 +.194
0 + 239 . 027 8. 850 +. 000827 .0000935 -. 000231 27. 7 - . 200
-10' +. 552 .074 7. 460 +. 00191 . 000256 -.000624 32. 4 -.540
-201 . 675 . 149 1 4. 530 . 00233 . 000516 -. 000863 36. 4 -.748
-30 . 727 . 209 3. 480 . 00252 .000724 -.000948 36.8 -.821
Stabilizer angle, + 10°
+301-0.182 0. 103\-1. 77 -0. 00063 1 0. 000357 1 0. 000461 82. 810 . 400 +20 - .064 . 0421-1. 52 -. 000222 . 000145 . 000321 168. ~ . 278
+10 +.119 . 026 +. 458 +. 000412 . 000090 +. 000061 - 14. n . 053
0 +. 436 . 051 8. 550 +. 00151 +. 00017651 -· 000367 24. 21-· 318 -10 . 689 . 1131+ 6. 095 . 00238 . 000391 - . 00068 28. 2 -. 590
-20 . 768 .179 4.290 . 00266 . 000620 - . 00087 31.9-.756
-30 .889 . 266 3. 340 . 00308 . 000921 - . 001063 33. 2 -. 921
i equals angle between chord of wing and wind.
Tail surface, No. 6.
Area, square foot, 0.1805.
E levator chord, 1.600 inches.
Chord, 3 inches.
Span (maximum), 9.25 inches
.
TABLE 13
Name of aerofoil: Tail surface No. 6.
Wind velocity: 40 miles per hour.
Authority: McCook Field 5-foot wind tunnel.
Date of test: October 161 1923.
Ele-1
I
I L/D I
I
I I i
vator L D K, Mc C .P. I Kx (LE) 3 IMJ. . E. angle · · chord
Stabilizer angle, -5°
+301-0. 749
1
0. 206 1-3. 63 -o. 00259 j+o. 000113 1 o. 000920 34. ~ +o. 797
+20 - . 6951 . 131 .-5. 30 - . 00240 . 0004M . 000801 32. 1 +. 6Jl4
+ 101 - . 526 . 0645 -8.15 - . 00181 I . 000223 . . OOOM8 29. 8 + . 475
01 - . 288 . 025 1-9.120 -. 00078 . 0000865'+. 00015 19. 8 +. 136
-10, +.109 .028 2.214 . 000214 . 000097 1- · 000223 109. -.193
-20 . 193 . 074 2. 610 . 0006681 . 000256 1-· 0004311 66. 9 -. 374
- 30 . 3261 . 128 2. M7 .00113 .000443 1-.000596 54.9 -.516
Stabilizer angle, -10°
I
+30 - o. 911 0. 271 -3. 36 1-0. 00315 o. 0009381+0. 001018 33. o 0. 935
+20 - . 778 . 166 -4. 68 - . 00269 . 000575f . 000805 29. 1 . 689
+10 - . 668 .102 - 6. 55 . -. 00231 . 0003531 . 000603 25. 8 . 523
0 -. 436 .049 - 8: 900 -. 00151 . 0001701 +. 00031 20. 3 . 268
-10 -. 086 . 026 - 3. 310 - . 000298 . 000090 -. 000143 - 46. 1 - . 124
- 20 +. 046, . 030 . 767 +. 000159 . 0002081 - . 000348 286. 5 -.301
- 301 . 163! . 107 l. 5231 .000564 . 0003711 - . 0004901 99. 5 -.425
i eq uals angle between chord of wing and wind.
Tail surface, No. 6.
Area square foot, 0.1805.
Elevator chord, 1.600 inches.
Chord; 3.00 inches.
Span (maximum), 9.25 inches.
Elevator hinge moments.
Tail surface No. 5.
'Lrnr,E 14
Air speed, 40 miles per hour, standard air.
Barometer 29.29. Hg. at 78° F .
<rested July 21 and 22, 1924.
McCook Field wind tunnel, test No. 111.
I Moment about hinge
Sta bi-lizer
Elevator Force
angle angle I Gross
----
Deg. Dey. Lb. I Inch Lb.
+5 0 + o. 0042 I +o. 0052
+5 5 - . 014:) I -. 0181
+ 5 JO - . 0250 -.0311
+5 15 - . 0450 I -. 0554
+5 20 - . 0630 -. 0761
+5 25 -. 0765 - . 0898
+5 30 -. 0945 -. 1070
+ 5 -5 +. 0185 +.0228
+ 5 -10 +.0280 . 0338
+5 - 15 . 0405 . 0476
+ s - 20 . 0650 . 0736
-10 0 . 0155 . 0191
- 10 5 . 0215 . 0260
- 10 10 . 0350 . 0411
- 10 15 . 0590 . 0668
- 10 20 . 0860 . 0931
-JO 25 .1055 .1080
- JO 30 0. 1345 0. 1290
-10 -5 0 0
-10 -10 - . 0130 -. 0162
-10 -15 - . 0235 - . 0293
-10 -20 -. 0400 - . 0492
-5 0 . 0110 . 0137
-5 5 . 0225 . 0277
-5 10 . 0330 . 0398
-5 20 . 0855 . 0968
-5 30 .1290
I
.1320
-5 -5 . 0095 - . 0119
-5 -10 . 0200 -. 0249
-5 -20 . 0470 -. 0568
TABLE 15
Elevator hinge moments.
Tail surface No. 5.
Air speed 40 miles per honr, standard air.
Barometer 29.29. Hg. at 78° F.
Tested July 21 and 22, 1914.
McCook Field wind tunnel, test No. 111.
Correc- I
ti on K et
I-nch Lb. Inch Lb.
0. 0043 0. 0095
. 0043 - .0138
. 0043 - . 0268
. 0043 - . 0511
. 0043 - . 0718
. 0043 - . 0855
. 0043 -. 1027
. 0043 + . 0271
. 0043 . 0381
. 0043 . 0519
. 0043 . 0779
.0043 . 0148
. 0043 . 0217
.0043 . 0368
. 0043 . 0625
. 0931 .0888
. 0043 . 1037
. 0043 .1247
. 0043 - . 0043
. 0043 - . 0205
. 0043 - . 0336
.0043 -. 0535
. 0043 .0094
. 0043 . 0234
. 0043 . 0355
.0043 . 0925
.0043 .1277
.0043 -.0162
. 0043 - .0292
. 0043 -. 0611
I Moment about binge
Sta bi- Elevator lizer angle Force angle I Gross Correc- ti on Net
- -- ----
Deg. Deg. Lb. Inch Lb. Inch Lb. Inch Lb.
+JO 0 +o. 0115 +o. 0142 o. 0043 +o. 0185
+10 5 -. 0095 -. 0118 .0043 -. 0075
+10 10 -.0200 -. 0250 .0043 -. 0207
+10 15 -. 0385 -. 0480 . 0043 - . 0437
+10 20 - . 0550 -. 0678 .0043 -.0635
+10 25 - . 0660 -. 0797 . 0043 -. 0754
+lo 30 - . 0870 -.1021 .0043 - . 0978
+ lo 25 -. 0660 -. 0797 . 0043 -. 0754
+ 10 -5 + . 0175 +. 0211 . 0043 +. 0254
+ 10 -10 +. 0290 . 0341 . 0043 . 0384
+10 -15 +. 0440 . 0498 . 0043 . 0541
+ lo -20 +. 0655 . 0710 .0043 . 0753
0 0 - . 0050 - . 0062 . 0043 -. 0019
0 5 - . 0250 - . 0311 . 0043 -. 0268
0 10 - . 0375 - . 0462 . 0043 -. 0419
0 20 -. 0705 -. 0828 .0043 -. 0785
0 30 - . 1080 -. 1169 . 0043 - . 1126
0 - 5 +. 0200 +. 0249 . 0043 +. 0292
0 -10 +.0300 . 0369 .0043 +.0412
I
0 -20 I +. 0550 . 0646 . 0043 +. 0689
0 0 I - . 0055 -.0069 . 0043 - . 00-26
0 2. 5 -.015.5 - .019:1 - 0043 -. 0150
I 0 5 - . 0215 - . 0268 - 004:1 - . 0225 ·o JO - . 037.5 - .04fi2 . 0043 - . 041!1
II ];') - . 0.550 - . 066~ . 0043 - . 0621 u 20 -. 0710 - . 0834
I
. 0043 - .0791 I 0 25 - . 0910 - -- -, ·1030 . 0043 -. 0987 -
0 30 - -.1095 -.1186 . 0043 - . 1143
I
I
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T ail surface No. 5.
TABLE 16
Air speed, 40 miles per hour, standard air .
Chord line of tail surface at 0° angle of attack.
Moments about elevator hinge at various elevator angles.
Tested June 6, 1924.
Elevator I Moment
angle Cos. Force =FXl.25 M,=M/880
cos.
--- - - --- - ---
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6 . 9945 . 0305 . 03792 . 0000431 8 .990 . 0356 .04406 .0000500 JO . 985 .0405 . 04987 . 0000567 12 . 978 . 0455 . 05560 .0000632 14 . 970 .0505 .06120 .0000696 16 . 961 .0560 . 06725 . 0000764 18 . 951 . 0620 . 07370 . 0000838 20 . 940 .0685 . 08050 . 0000915 22 . 927 . 0760 . 08805 . 0001001 23 . 920 . 08LO . 09315 . 0001059
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back of elevator hinge.
Area or tail surface =0.18332•
Chord=3 inches.
Span=9)4 inches.
'.!'ABLE 17
'l'ail surface No. 5.
Lift forces at various angles of attack of stabilizer with elevator at 0°
and with elevator free in neutral position.
Air speed, 40 miles per hour, standard air.
Tested July 23, 1924.
McCook Field wind tunnel test No. Ill.
Lift Force
Angle of
attack of
stabilizer Elevator Elevator
I at 0° free
Deg. Lb. I Lb.
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Description

Title	Wind tunnel test of six horizontal tail surface designs having the U.S.A.-47 airfoil section (Airplane Section report)
Author	United States. Army. Air Service. Engineering Division.
Date Issued	1925-06-01
Series Information	Air Service information circular (Aviation) ; v. 6, no. 511; McCook Field report ; Serial no. 2463
Description	The object of this test was to determine the effect of plan form and elevator size on the aerodynamic characteristics. In addition, the variation of hinge moment with elevator angle was determined in the case of one design.
Subject Terms	Aeronautics--Research; Aeronautics--Systems engineering; Airplanes--Design and construction; Wind tunnel testing; Airplanes--Parts--Testing; Airplanes--Tail surfaces; Aerofoils; Elevators (Airplanes)
Report Publisher	Washington, D.C. : Chief of Air Service
File Name	asic511_ocr.pdf
Document Type	Text
File Format	PDF
File Size	20.9 Mb
Document Source	Auburn University Libraries. Government Documents.
Digital Publisher	Auburn University Libraries
Rights	This document is the property of the Auburn University Libraries and is intended for non-commercial use. Users of the document are asked to acknowledge the Auburn University Libraries.
Submitted By	Coates, Midge
OCR Transcript	AT\NG Auburn University Libraries llllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllllll N 3 1706 025 85062 4 File D 52.32 / 2 7 McCOOK FIELD REPORT, SERIA.L No. 2468 Vol. VI 0° 5 ¢ \ '~ ~ '\ i;:; MCC'OOI( FleLLJ s F'T G 0 A ,... WIND TUNNel \ " ~ 1\1 :\ re.srco 8{& -aI ;ea \ "\ j .. _, \ 1a'9-IO/Z3 \ ~ \ \ I~ \ '~ \ \ ·- \: ~ \ \ \ ~ ' ~\ ~ \ \ ' ~ \ \ I \ -;; \ \ \ II: \' .\, 'L_~ ~\ . - -~ ~ \ \ \ \\ \ o I .. '\ \ \ ~\ \ '\~ \ \ \ ~ \ - \ ,, \ ~ \ \ ~ \ \ \~ \ \ \ ~ \ .. \ ~ \\.. ' i\ ·- 'I._ ~ ~ \ "\ ... I\. ~ ~ ~ ....... I'... ~ ~~ ~ ~ ~ -A ~ ~ ~I r::-y, ~Ti he> ~INf. ~I J. - I 111~ '(.;) ,~ ~ '.~ -- __ ... h -z. ~ -JO ( ~ in ?() ~ ·- ,b 0 F IG. 8 10 Tfi!L SURFflCCS(HOR.) TAIL G /)/ffe!!ZNT TAIL "URrRCC:.'1 SURrRce !YO Or RLl1a5T eQURL TOTfJl J 0 R~E.R Bt/T Or Yfili!JOUS z }( SHRPeS f/ND %'s Or f:LeVfi- 3 A 4 + ro;e flRER ro TOTAL flRl!fJ s ~ ~JR S~t:D 40 /'1.f?H. 6 a STABIL/ZO! @ 0° J11C'C001( rtelO 5rT.' WINO T'l/NNeL tJ/4 - tj/Z.3 DATeOrTEST 10/s- 10/~ ,, I\ \ z I\ 1' 13ll Iii -J/1. ' r\. r JI ,,,, ~ \ I// I s ,. ~ \~ I\ A rt/ / \. "' ..., J ,,, ,,, \. I\ (/ 4 - " ~ \ /) ·~ v -- ' " '\·, \ V; 'J ,.v - ' " ~ ' I /) ,./ " . r\. " ''I ~ \ h v~ V' -~ U') J ·- ...... ,.....i '-......"\: ~ I\. /,;,: ~II' - (! "~ ~ ~ ~ ·- ~ ~ N' ~ ~ ~ ... .., \,,, "'11111 ~ ~ .....:::; ~ ...._ ·- .........:: ;..- • ,.. t: If ·--- ,, J~E7 ill\ r. ff 1Jf:J': - -~ () -J t) ' Jit7 !!In 'Ill: FIG. 12 14 TABLE 7 Name of aerofoil: Tail surface No. 4. Wind velocity: 40 miles per hour. Authority: McCook Field 5-foot wind tunnel. Date of test: October 10, 1923. L D TABLE 9-Continued L/D Mc (L.E.) EleC. P. vator a ogle 3 ML.E. chord E le- 1 I I I I v a tor L D L/D K, K, IM c(L.E.) I C3. P. I ML.E. an gle chord ' Stabilizer angle, -10° HO -o. Bl?4lo. 211\ -4. 190 -o. 00'.2".J70lo. 000109 +o. 001050! 35. 30 o. 936 +20 - . 7o3 . 140 -5. 380 -. 002030 . 000471 +. 000846 32.90 . 755 +10 -. 643 . 0861 -7. 480 - . 002!60 . 000289 +. 00062~ 28. 70 . 559 0 -. 468 . 0501 -9. 360 -. 001073 . 000168 . 000360, 23. 10 . 326 -10 -. 223 . 034 - 6. 855 - . 000784 . 000114 -. 000012, -1. 56 -.011 -20 - . 125 . 047 -2. 660 - . 000420 . 000158 -. 000189 -49. 00 - . 169 - 301 +. 022 . 070 +. 3141 +. 000074 . 0002351 -. 0003681 122. 00 -. 329 Stabilizer angle, + 5° + 30 -0. 252 1 0. 081 -3. llOi-0. 00084710. 0002721+0. 000568 69. 51+0.' 507 +20 - . 103 . 045 -2. 290 -. 0003461 . 000151 +. 000342 105. 0 +. 305 + 10 +. 053 . 025 +2. 120 +. 000118 . 000084 +. 000099 -54. 2 +. 088 0 +. 268 . 024 + ll. 160 +. 000901 . 000081 - . 000254 28. 01 -· 227 -10 +.460 .048 +9.58{_ll +.0015501 . 0001611 -.000550 35. 4 -. 491 -20 +. 607 . 098 +6. 190 . 002040 . 000329 - . 0008ll 39. 3 - . 724 -30 +. 688 . 146 4. 7121 . 002310 . 0004911 -. 000938 39. 9 -. 835 i equals angle between chord of wing and wind . Tail surface No. 4. !\rea, square foot, 0.186. Elevator chord, 0.965 incb. Chord, 3.00 inches. Span (maxcimum), 9.25 inches. TABLE 8 Name of aerofoil: T a il surface No. 5. Wind velocity: 40 miles per hoar Authority: McCook Field 5-foot wind tunnel. Date of test: October 15, 1923. Ea tloe-r 1 ngle v a L I D I L/DI I I I I C.P. K, K, [Mc(L.E.) 3 ML.E I chord Stabilizer a ngle. 0° +w _, ..,1 " •+• ~L, "''[" ""'" H ..,,. 42. 9 0.620 +20 - . 3441 . 073 -4. 710 - . 001180 . 000250 +. 000512 43. 5 . 449 +rn - . 243 .034-7. 04ol -.ooo830 . 000118 +.000340 40.8 . 298 0 +. 005 . 016 +. 3031 +. 000020 . 000056' - . 000040 231. 0 -. 035 - 10 +. 209 . 039 + 5. 2901 +. 000720 . 000135 - . 000337 47.1 -. 296 -:io +. 343 . 081 + 4.2421 + . 001!40 . 000277 -. 000542 46. 0 -.476 -301 . 460 . 124 +3. 6931 +. 0010801 . 0004261 -. 000715 45. 4 -.62ll i equals angle between chord of wing and wind. Tail surface No. 5. Arca, square foot, 0.1825. Elevator chord, 1.285 inches. Chord, 3.00 inches. Span (maximum), 9.25 inches. TABLE 9 Name of aerofoil: Tail surface No. 5. Wind velocity: 40 miles per hour. Authority: McCook Field 5-foot wind tunnel. Date of t est: October 15, 1923. I Ele-1 I va- C. P. tor L D L/D K, K, M c 3 ML.E. 1 (L.E.) chord a nglel -- --- --- Stabilizer angle, +5° - ·--~- -- - -· + :01-::_o. ~111 ~- tJ?l I - 3. 027 - 0. OOO«1 + IO -. 044: . 0241 -l. 7J - . 0001501 . 0000841 +. 000190 ltiU. 2 0 +. 260 .0251+10.200 +. 000890 .0000871 -.00U24fl 27.[>U -o: IO +. 51\11 . 063 +8. 237! . 0017801 . 0002_Hi -. 000598 :33.f> ~ 20 . +,_ 620:_ -127, +4. 880_ .-002120 . 000430 - . 000805 37-. 3 .. - 30 +. 699 . 176 3. 960 . 002400 . 000605 - . 000943 38. 7 I . I _ , _ ___ · __ _ ·- 0. 489 . 320 ~:m / -.525 - . 706 - .827 Stabilizer-angle, +10° +30 -o.095 0.077 -1.225 -0. 000330 0.000265 +0.000435 +20 +.036 . 046 +.783 +. 000120 . 000158 +.000238 +10 +.158 . 025 +6.195 +.000540 . 000087 +. 000066 0 + . 450 . 050 +9. 000 . 001540 . 000171 -. 000364 -10 +.663 . 101 +6. 565 . 002270 . 000346 -. 000670 - 20 +.761 . 161 +4. 710 .002610 . 000553 - . 0008691 -30 +.873 . 227 + 3. 838 . 002990 . 000780 -. 001071 i equals angle between chord of wing and wind. Tail surface No. 5. Area, square foot, 0.1825. Elevator chord, 1.285 inches. Chord, 3 inches. Span (maximum), 9.25 inches. TABLE 10 Name of aerofoil: T ail surface No. 5. Wind v elocity: 40 miles per hour. Authority: McCook Field 5-foot wind tunnel. Date of test: October 15, 1923. Ele- I I va- L D L/D I K, K, Mc tor I (L.E.) angle I Stabilizer angle, -5° +30 -0. 713 0. 1681 -4. 230 -0. 002440 0. 000577 +0.000925 +20 -. 575 . 1111 -5. 730 -. 002180 . 000380 +. 000778 + 10 -.498 . 0541 -9. 225 -. 001700 . 000185 +. 000553 0 -.246 . 024 -10. 040 -. 000840 . 000084 +. 000188 -10 -.036 . 027 -1. 333 -. 000123 . 000092 - . 000153 -20 +.150 . 061 +2.458 +. 000510 . 000209 -. 000411 -30 +.264 . 0951 +2. 780 . 000900 . 000325 - .000572 Stabilizer angle, -10° +158.8 -169. 6 -12.0 +23.6 29.1 32. 6 34. 8 C.P. 3 chord 37.3 35.3 32.2 22.2 -118.06 84.0 65.5 +301 -. 888 0. 221 -4. 010 0. 003040 o. 0001581 +o. 001035. 33. ii + 20 -. 760 .147 -5. 150 . 002600 . 0005051 +. 000836 31. 5 +10 -. 654 .091 -7.190 . 002240 . 000312 +. 000616 27. 3 0 -.452 . 049 -9. 225 . 001550 . 000168, +. 000346 22. 31 -10 -.140 .027 -5.185 . 000480 . 000092 -. 000121 -25. 0 -20 -.040 .053 -. 755 . 000140 . 000182, - . 000272 -165. 5 -30 +.080 . 080 +1.000 . 000270 . 000270, - . 000433 + 197. 5 I i equals angle between chord of wing and wind. rl'ail surface No. 5. Area, square foot, 0.1825. Elevator chord, 1.285 incheo. Chord, 3 inches. Span (maximum), 9.20 inches. TABLE 11 Name of aerofoil: T a il surface No. 6. Wind velocity: 40 miles per hour. .\uthority: McCook Field 5-foot wind tunnel Date of t est: October JG, 1923. 0. 382 . 209 . 057 - . 319 -.587 -. 762 -.940 ML.E. 0. 811 .682 . 458 +.165 -.135 - .361 - .502 0. 908 . 733 .540 . 303 - .106 - . 239 -. 380 vEatloer- 1 angle L Ky Mc (L. E.) I C. P. , 3 ML"' · chord Stabil izer angle, 0° +30\- 0. 5201 o. 1501 1 -3. 33 -o. 00180 \o. 000540 o. 000117 38. 5 o. 622 +201 - . 382 . 092 -4.15 -. 00132 . 000318 . 000527 41. 3 . 457 +10 - .311 .042-7.40 -.0010761 .000145 .000399 37.0 .346 oj -. 001 . 019 -. 0525 -. 000003 . 000066 -. 000024 - 697. o -. 021 -10 . 3041 . 0491+6. 205 + . 001052' . ll00170 - . 000441 41. 9 -. 382 -20 . 3651 . OYG 3. 800 . 00l26:l . 0003:12 - . 0005.;6 43. 9 -. 481 - 30 . 4!!5 . 15fi 3.1\1:3 . 0017~~ . 000537 - . (l(J0725 42. 2 - . f\28 i equals angle between chord of wing and wind. 11ail surface, No. fi. Area , square root, 0.1805 .. Elevator chord, 1.r.flO inches. Chord, 3 inches. Span (maximum), 9.25 inches . 15 TABLE 12 Name of aerofoil : 'rail surface No. 6. Wind velocity: 40 miles per hour. Authority: McCook Field 5-foot wind tunnel. Date of test: October 16, 1923. Ea tloe-r 1 ngle v a L I D I L/D I I I K, K, Mc IC. P . I (L. E.) 3 ML.E. chord Stabilizer a ngle, +5° I +301-0.340 0. 124 1- ?· 74 -0. 001176 0. 000430 +0.000581 51.1 0. 504 +201 -.218 . 0685 -3. 18 -. 00075 . 000237 . 000409 56.1 . 355 +10 - . 091 . 025 -3. 64 -. 000315 . 0000865 +. 000224 72.8 +.194 0 + 239 . 027 8. 850 +. 000827 .0000935 -. 000231 27. 7 - . 200 -10' +. 552 .074 7. 460 +. 00191 . 000256 -.000624 32. 4 -.540 -201 . 675 . 149 1 4. 530 . 00233 . 000516 -. 000863 36. 4 -.748 -30 . 727 . 209 3. 480 . 00252 .000724 -.000948 36.8 -.821 Stabilizer angle, + 10° +301-0.182 0. 103\-1. 77 -0. 00063 1 0. 000357 1 0. 000461 82. 810 . 400 +20 - .064 . 0421-1. 52 -. 000222 . 000145 . 000321 168. ~ . 278 +10 +.119 . 026 +. 458 +. 000412 . 000090 +. 000061 - 14. n . 053 0 +. 436 . 051 8. 550 +. 00151 +. 00017651 -· 000367 24. 21-· 318 -10 . 689 . 1131+ 6. 095 . 00238 . 000391 - . 00068 28. 2 -. 590 -20 . 768 .179 4.290 . 00266 . 000620 - . 00087 31.9-.756 -30 .889 . 266 3. 340 . 00308 . 000921 - . 001063 33. 2 -. 921 i equals angle between chord of wing and wind. Tail surface, No. 6. Area, square foot, 0.1805. E levator chord, 1.600 inches. Chord, 3 inches. Span (maximum), 9.25 inches . TABLE 13 Name of aerofoil: Tail surface No. 6. Wind velocity: 40 miles per hour. Authority: McCook Field 5-foot wind tunnel. Date of test: October 161 1923. Ele-1 I I L/D I I I I i vator L D K, Mc C .P. I Kx (LE) 3 IMJ. . E. angle · · chord Stabilizer angle, -5° +301-0. 749 1 0. 206 1-3. 63 -o. 00259 j+o. 000113 1 o. 000920 34. ~ +o. 797 +20 - . 6951 . 131 .-5. 30 - . 00240 . 0004M . 000801 32. 1 +. 6Jl4 + 101 - . 526 . 0645 -8.15 - . 00181 I . 000223 . . OOOM8 29. 8 + . 475 01 - . 288 . 025 1-9.120 -. 00078 . 0000865'+. 00015 19. 8 +. 136 -10, +.109 .028 2.214 . 000214 . 000097 1- · 000223 109. -.193 -20 . 193 . 074 2. 610 . 0006681 . 000256 1-· 0004311 66. 9 -. 374 - 30 . 3261 . 128 2. M7 .00113 .000443 1-.000596 54.9 -.516 Stabilizer angle, -10° I +30 - o. 911 0. 271 -3. 36 1-0. 00315 o. 0009381+0. 001018 33. o 0. 935 +20 - . 778 . 166 -4. 68 - . 00269 . 000575f . 000805 29. 1 . 689 +10 - . 668 .102 - 6. 55 . -. 00231 . 0003531 . 000603 25. 8 . 523 0 -. 436 .049 - 8: 900 -. 00151 . 0001701 +. 00031 20. 3 . 268 -10 -. 086 . 026 - 3. 310 - . 000298 . 000090 -. 000143 - 46. 1 - . 124 - 20 +. 046, . 030 . 767 +. 000159 . 0002081 - . 000348 286. 5 -.301 - 301 . 163! . 107 l. 5231 .000564 . 0003711 - . 0004901 99. 5 -.425 i eq uals angle between chord of wing and wind. Tail surface, No. 6. Area square foot, 0.1805. Elevator chord, 1.600 inches. Chord; 3.00 inches. Span (maximum), 9.25 inches. Elevator hinge moments. Tail surface No. 5. 'Lrnr,E 14 Air speed, 40 miles per hour, standard air. Barometer 29.29. Hg. at 78° F . --l----1---Hk---l---+1---1-.;...i--;.1---1-Hr+-i:---+-l ti i l i l I I l '""- • 1 ! I I ! 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Wind tunnel test of six horizontal tail surface designs having the U.S.A.-47 airfoil section (Airplane Section report)

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