Supplement to Index to unrestricted U. S. Army Air Corps Information Circulars nos. 601-657 inclusive

              I Auburn University LibrariF>s
-1/ . //
File 013/117/1931/Jan.15
/"J g7. '' (-i-"- l> /1, (ftJ I ~llf P-
111~m1~1m1~1~~~~~
3 1706 025 85126 7
AIR CORPS INFORMATION CIRCULAR
Published by the Chief of the Air Corps, Washington. D. c.
VOL. Vl
\ b Brown oraug\\on
Ra p L\SR~R'l
\"\J\'{ 2 8 10'3
Non·Oe\lo\\OY'IJ., i
~unurn Un\\lersh
January 15, 1931 No. 600 Supplement
SUPPL.EM.ENT TO
I N D E X
. to
UNRESTRICTED
U. S. ABMY AIR CORPS INFORMATION CIRCULARS
NOS. 601 to 657 INCLUSIVE
U-1003,A.C., 1/15/ 31
li~DEX TO UNRESTRICTED UNITED STATES ARMY AIR CORPS
. .... . ~.· ' ; .. :
···'· · .· .. ·.
I NFORMATION CIRCULARS
,>
Nos. 601 - 657 , Inclusive
~ . .. .,,
. 1: :: .·~· -· .- .._ .......... '·. : .. · ..:. • <I.
. . . ~ . ~ ', ..f . .. --:. . ·. .·
SUBJECT LIST
.... '' .. ,,; _,• ... :.·.·· ·; ..
. . . . . " ' . 4 . .. :
. · . _. iI?-;f:.o~tion
· Circular No .
Accidents, U.S. - Sta~i~~ical ~.~udy 9f ~ir~rB:-ft. Accid~nts
· · a11.d Fotc~d Landii1gs ·~ -~ · -~ - -. ··. - .<· .. · . ·-,_. . " 652
. ·. . ~ : ..
Aerodynamic Chords, Deterraination of Center of_ Gr:avi ty and .. Mean A~rodymirri1i{ · ciio~ci • • . • ; • -. .: ·
. . . . . · .. : . ·_ :. ·:·1 '.· ... ... . ... : . .. .. ·. f.' . .. .
···i-:.'605
Aircraft Igni tio:i, Recent Devel_o:p~ents. . • . 6L!.
. . :· .... · .. .: ·: ,: . .-. · .. '.1,. . , __ ..... ·
-~ . .. ·Airplanes: · · · .. · · · : ... ,.. ... · · '· ...
Consolidated PT-3, Study of . Horiz~~1tal T.ai~ Surfa~es of . ..
..
Desi gn , Miscella;.1eous Collected_.Air1)lane Structural De­s.
i gn Data Formulas ~nd Me thods •.. ! . . .... • . . . . : . . . . . . ' . :·. . . . . · . . 644
DH•4B, Wind Tunnel Tests of Model Fitted with Various Fins
and Rudders · . · .: ·~ -• ' .· . ,. . . : . . . . • . " . · . . : -603
Design · of Trussed. Metal S1)ars fo'Z.. single Eay ~ ';-- ~ " • . ; .. • 621
DetenninatJ..on :.of . St~bfl.i'ty ·from :ir1ight Test . stick' Fotce·'Data · ·625
Determi_nation 9f .S tructural A~r:plan.e Drag! • _, .. .. .. . , _._ : . ·.. " .
Effect of c ·ellule 'Aria1igein~1~ t- ~fr · the Rate ~ 6f Aut6~otatlcin -
by th~ St~ip Method • • . • . • . . • . •
I~duced Drag of Anl·Eiplane ~ ... • • ; . .: ·. . .I .
Observatio1-i., Wi:iid. Ttinn.el Te.st of i/ 20 'S·ca.-le · Mod~l · o:t the
629'
609
. I'
607
Materiel Division· lUght · Observation·Airplane. · • · •• : 610
Rigidity and Flexibility of Airpla~e St~icture s.
" .
Spinning .Characteristics . • . . ~ ,. . .. . . ... '
Analysis of Aircraft Accidents. • ~- • • . • . . • • . •
I' -• •• • • • : •• • ~ : • : ;. 1 •
Autorotatiotl Calculated· by the Sti-ip Method; "Effect of":·
Cellule Arrangement on the Rate of •••••.•
. :B
Beams: Precise Formulas for Restrained J3eam with Axial Load
: •, .. 642
613
· ..
609
- . .. . . .. . ·-
of.Compression and with One Res training Moment Knovn1. • 624
- 1 - U-1003,A.C., 1/15/ 31
Biplanes: The Induced Drag of Any ·Biplane
c
Information
Circular No.
607
Calibration Constant of Wright Field Fiv~-Fo ot Wind Tunnel. • 643
Carburetor: NAY-60, Dynamometer Calibration Runs on Curtiss
GV-1570 Engines • ~ . . • . • . • . . • • . . . . • 630
Cellule: Arrangement on the Rate of Autorotation Calculat'ed
by tl:ie Strip Method of • . • • • • • • . • . . . . . . 609
Celluie: Consoltdated PT-3 Airplane Wing Cellule in High and
Low I11cidence. . . . . . . . . . . . . . . . . . . .
Cellule: Wind Ti:tnnel Test of 1/24 Scale Model of the Douglas
0-2E-l Airplane Wing Cellule Through 360. Degr.ees
Cowls , Wind Tunnel Tests of Venturi TYJ.)e Cowls and Engine
~acelles Sui table for Multi-engine Airplane • • • ·•
Crashes, Analysis .of .Airplane Accidents
D
Dopes , Airplane Doping and Dope Room Requi:r:ements .
Drag,· Determination of Structural Airplane Drag • ' ..
Drag, Induced Drag of Any Biplane ~ • • . . . . .
Dynamometer Carburetioi1 Runs on Curtiss GV-1570 Engines .. . · ••
E
Elastic Axis, Determination of t~1e Elastic Axis and Natural
626
612
!·
629
633
655
629
607
630
Periods of Vibration ·of the Atlantic C-2.A. Monoplane Wing. 645
Elastic Axis, Static Test and Determination of the Elastic Axis
of the (Matede;I. · Div.) Improved Stressed Skin Type Glider Wing 646
Elastic Weights, The Computatioi+,.' of Truss Deflections by the
Method of • • . • • • • • . • • • • • . . . . . . • • 620
Engines: ·
Curtiss - GV-1570, Dynamometer Carburetion Runs on • • • • 630
L.iberty - 12, Test of Standard. Water-Cooled Engine with
Various Pis ton Rings and .Arrangen1ents. • • · • • • 638
.... 'F
Falling Man, Determination of the Rate of Descent of a Falling
Man and of a Parachute Weight • • • • • • • . • •. . • • 628
Fatigue of Metal propellers Caused by Engine Impulses and
Vibration, Prelimii':rary .. Study of • • • • • • . • • . • . • 618
,
- 2 - U-1003,.A.C., 1/15/ 31
Informat i on
Circula r
Fins, Wind Tunnel Tests of DH-413 Model Fitted with Various
Fins and Rudders . .. \:~,:;: •· .:. ··.. . . . • . ... . . .., . . . · . . . ,
' • ' , ; ,·'I
Flaps, Resume of Investigation Made on Handley Page Slots
and Flaps • • . . . . . . . . . . . . . . .
. ·' ,- ,
Fli ght Test Data,. Determi.nati.on of Stab ility ·:f .rom .' ... ~ ...
Flood Light:
A-2 and A-3 ; Harndbook .:Of 'Insttu.c:tions. Jci.r A.1rdrome . • .:~ •
A-4, Handbook of Instructions for Airdrome Landing Field
T.est at Fair.fi.el.d Air nepo.t •. • • . •. •.
Formulas:
Miscellaneous Ccillected .. Airplane .Strltctural Design: Data
·:- Formulas, . ru1ci Methods . •. ,,· .. •. ·:-• .... :~ i · ·· · ~ , .• ·; .• . ._ , .. , . - . • •• .
Precise Formulas for Restrained Eeam with Axial Load of
Compression, and with One Restraining Moment Known ••
Gauge ·Set The McCol-lum-Pe-te.rs· Si:x: Element· Tel-emeter S·train
Gauge Set • • . . • • • • • • •
·' . . . ..: ~) :. : ; .:,- ' ': .... : ': ~ -~ .. :- : •. ;;_ , ,· ...
Gliders, Statac. Tes.t and De-tenninat-ion of ·Elai:;"tit Axis" of' the"
(Materiel Div.) Improved Stressed Skin TYl)e Gl. ~der Wiil:_~·
, . · ·. r . i. ~: ··:. _. . ... •.
Gravrty, Determination .of. the ·Cen:tet- -of Gravity and Mean ·· -
Aerodynamical Chord • . • .
.. .. ~- -
6d3
639
' 625
601
606
62:3
." 6'-14
624
657
646
605
.. '.-. ..
I
Igniti on: Aircraft, Recent Developments In. . ; _-. 611
··-: . I~ ;; .i . . • .. :: . . ::
. . ~- -:.. ~: : : ... L ... ·, -, ... ~: "-. -·
Landing Field Flood Light:
A-2 and A-3, 1landbo~6k .. ofr Instr.u'6:t:i ·bns 'for Airdrome· • ," \ ·:._:,•·,.-. . 601
.A.- 4, Ha.n-tj.bo'ok-- of'' I.n:s tr.Uc t idnsJ .f:'oi'.. • • . .; - -
· · • • • 4 • • • ·• • I • • ·; : .. ' 606 -
• i ~ . . . .. t :
Landing Gears, Determinati on of Stresses in Landing Gears and
Design of ·Shock,:)\.bsorbing ~ U-ni t.s · .• · •.• ·• · • :, ;. _;· . -. • . . ~ ·· . · • . 602
~ ..... . . .. . . . ,•
Least Work Method to the Evaluation of Initial and Tem~erature
Stresses, Application of the ••• :; · •. · ... · • . • . • 634
. - . ! ·: .:;·· .. 1'• ·· . . . .~ : : .: :. .• . ~ . j .:
Loading - Test of .Armstrong.,-Whitworth. Steel. Spars- Under Com-bi
ned Axial and Transverse Loading. • 656
Loads:
Precise Fornmlas . for Restrained Beam. with Axial Load" o'f 0orn-'> _
pressi on, and with One Restraining Moment Known. • • • 624
No.
:-·.£ ·.~·;; :· :·_.·_.\· .• ·.:" (i. _:·t .'·: ; :;·~:. ~-::.·· ~ .:··. - ·: . :. · ··,; "." .. ·. : -.. .. ·,~
. . . . - . 3 . - . -~ · U;-1903·.A. r;, :<, J,/ 15/ 31
\ ·~ \ .. ~ ~ ' .. ' :. ~ . .; . -·
.!· lnformation
Circular No.
Loa ds (C ont·1d): · · " " •'· ·" ' ~- i :· :-. ·,:.'.:~ ..... . ,.._ .
' • • •·• I ! . ~ . . ; •
Proposed Method df ·Determining ·Design Tail ·Loads' ·f'o·i-- :-: ... ~ t:
.Airplanes •. .. • • . • ';· . . • . • . '.. • • . . •. . • . . • 650
:-: :. ·~ '
M . :.··
Millivolt-Temperature Relq.t~o~ qf the Standard .Air Corps I_ron.- . . ..
· ' Consts.ntin Therrn-Ocoupie '< · :: ..•... · · ... ' ·· · .• · ~ - '·· , ... .. 654
. ..
N
Nacelles, ·Wing Twiirh : T·es.t' -'·of 'veri turi . Ty-pe C o;.,f~· ·aii.d E~gine · . .
. Nacell~.s ,S.ui t~b~e /?;.,.¥.17-~~~-~~~ii;ie :A~ ~},a,ne!?_. :.. • .· . ·,.· · • ..
• • . •. • • • ... • .• •• · • ... ... • • ~· • • . ...... l •1 , • • • • ... • - ..
647
Nomogra:phic Column Charts with Isobars . of Weight ~.n4 . T~ns_ile
St ·t,,.. ' ' ..... ' ' .. .. . : .. reng . ; . . ...· . ' . : . ..~ '.h.. ' ·~· 631 .LJ.. .. • • • • • • • • • • • • • • • • . · • • - .- • · • · • •
. .. . .. - . . 0 .. . ' - .. .
." . ..- . ·:. .... ..-.·.. ,. . ::_
ous, Relat"ion of fuboratory:·:1iests --a'.nci 06-la "Weath~r Mote~. ..
Operation·of Various Clils; Ft ; 2. ·. ·• - ~ > . ·.<· :. < ..... ~.. 640
;: .. .·: .' ... ,._:·]?.> ... :. · ';"~''.: '. .. . .. -~.;. :. •.' .. . ,·! .. • . t . _ •
• . . ... .. ..
Para chute:
• :. ]·;· . :· .. _. •• .• #. • ... : · .': • • -: :.: • .: :·. ••• t · - .• · . ... •·. ·" '·'
Cloth, Physical Characteri stics{·under Varying Atmospheric
Co tlcii ti onS ~ :: :; · ·:.:· .:· ·. -_· . .-- . · ·. ;~ · -~- \.: . ·· •· ;.:-. . ·; { ; ,,. :;:-- ·.'. __·- : ·' ~ _. .. . · .. .. ·--~· .: . .. . · :" ~;
Weight, Determination' of the Rate of Descent of a. Falli~ g
Man arid o:f;.g_. Parach'1te Weight· ' i :-.·, ' . ~ .:~ ·< ·; ·. ·. ·: .. . · ;..- ' ':·.: 628
f . •. ~." -.= .. -~._:_: ._ ': ' ·: .. >· .·'. .. : -.;! .·. :.: ;:'_':;·: :- :·:·. - ~ ;. • . ~- - ...
Piston Rings, Test of Staridard Water-Cooled Liberty-12 Engine
with Various Pis tori. ·Rhi~s :·a.na Arrangements. <- : ~- '• ·-.. ·, • .:~· '..-. 638
. . . .. . . . . . . . . . . ~ -~ '._.:·, .;: . . - .
Pressure Dis t ribution Data, Study of •. • • 604
Propeller: · · · .; <~ : .: .. .,, - .' -,. -, .... .. : · '.. .:.: .· · ·
Comparison of Wind Tunnel Tests .with Flight Test of a Number
of Detachable Blade Propellers Made from ~~e . sam,e f~an FoI'Il;l 632.
! . . - . . . .. . . . . : :: :. . . . ~ ..
. . . : ,... . . - :. . . " -· i . .. . . . . . . .. . .
Instru~tions for · Assembly· of ·Detadhcible .. Blade Propeliers ·" · ·· ·'648
J?relim:l.nary · St1ld;}' of· Fatigue · ·Of ·Metal l?ropeiier~ Caused by ,.' -- ... Engine Impμlse$ anQ. Vibrations •. •• ! • : •• • : • ••• .
' ' • • <' • • :~ "'_, • : •I ' • ' • • . ' -. .. t ..... • ,' ' ' • ~ ;-:.::. • . • · - <o • '
6l f?
Section Prbperties · of a Series' ~:f< Airf~iis SO.i table f or': ~-- :.· ·
Pr.~?Ef~l~r ._D~s_i~ I : ~ . _! ,·: -~ : , . • ,. ~ ~ .;.._.'. y !~-,.-~ .:._.;.;- .:. ,' • .i. -~ ,: j_. :'·'. ."·: _ ~. . •. 5.97(
. 'l .. •. :
. . . . .. . . . . R . . "· ~ ~ . . :· : .; .. :· .:0---.'., ·.. ' ;.: . .. ·:. ·.
Rudders, Wind T\Ul!l,el Tests of DH-413 Model Fitted with Various
Fins . and Rhdd.ers·. ·. .. . ". >. :-. ~ .> " ;:·:. ~ .. :'~ . ·. ··. .. . ... :. '<.. _< . 60J
• .. • • • • • • • • .. " • ; :· • • •• ·:·. • • : : • • ,.J £ . ·~.:·. .. .~ . :·
s
Section ~r.operties of a Series of Ai rfoils Sui table for : "' : .:· :->
Propel ier Design. • -. -. . • :: • · ". · ... :- -. ~-~ _. .. ,. · . .'; -: · ·. . -~,,: ~- ! • .-: '£ ·::597
' _.-
. ·: ~- . . . . ..
Shock Absorbing Units, Determinat ion of Stresses in Landing Gears arid D~sign of • . . • • .. • _-· . . . • • . . . . . • 602
- 4 - U-1003,.A.C.,l/15/31
Ski, Airpl~ne, Sta tic Test Report of Type E-1 .. . ... .
I nforma t i on
Circular No .
636
Slots , Res11ffi:e .of I.nves t igati.ons .Ma de 011 .Handley ·Page Slots
and Flaps • . . . . . . . . . . . . . • . . .
Spar:
Desi gn of. T_ru.ss~d Metal SJ?a rs for Single Bay Airplane. •
Supplementary Re1)ort on . Tests of.~ .~ _ Inch Metal Spars ••
T·est of Arr.astrong- ¥fai t worth Steel Spars Ui1der Combined
Axi al .. and Transverse Loacling: ·
T~sts on ~ Inch lvietal Spars •
Spimdng, Cha,raderistics, Airplane •
Stability, Determination of Stability fron Flight Test
Stick Force Dl:l-ta.~ · . - • · •. • . • . . • . • • . •
Stick Force Data, Determination of Stability from E'li ght Test·
. . ; · · .·
Stresses:
The All.owabl.e Stress : in. Tub:es Subjected to Torsion.
Application of . the · L~a~t Work Method to the Eva luation of
Initia l and Temperatur~ Stresses • · . ~ • . . • . • . . •
De t -erminat:i.oi1 of Stresses in La.~1ding Gears and Design of
S~oc_~ J\bsorbing Uni ts. · • . • • ~ • ~ •' • • . . . . · . . •
. . . . . .
Revised Nomo graphic Column Charts with Isobars of Weight
and !])ens..ile Strength • • • • . • . .. . -.•
T
Tail Loa ds, Proposed Method of Determining De~i gn Tail Loads
639
621
637
656
622
613
625
625 '
641 '
634
602
631
f or Ai r planes .• : • - • . • . . • . . • . • • • . • • 650 ·
Tail Sur face: Study of Horiz ontal Tail Surfaces of Consoli­dated
XPT-3 (NY-1) •• · •• ..• ~ .• . ; • •.••• • .• •
• • •• • t ••
~ . . . '
Telemeters - The vicC ollum-Peters Six Element Telemeter St rain
Gauge Set ·· . ·. ~ . ~ . · . . . . . . . . . . . . . . . . . ·. ·
Temperature, Application of t he Least ·fork Met:1od of . th$
Evaluati ono:f Initia l and . '. ........ • •
Thermocouple , Mi llivolt - Temperature Rela tion of the ·standard.
Air Cori)s I.ron-:Constantin .. .. .. .. .. • . . . . • •
Torsion:
All'owable Stress in 'I'ubes Subjected to Torsion • . • . .
615
657
654
6.41
Tors i on L1 [ul-tispar Cant .ilever Wings, Some Asp~Cts o:t' • 627
- 5 - U-1 06 3,A.C~,l/15/ 31
Truss Deflection, The Computation of, by the Method of
Information
Circular No.
Elastic Weights ~ · •. . • ;. . . . . • . . :020
Trussed Meta l Spars for Single Bay Airplanes, Design of 621
Tube: Allowable .. Stress in Tubes . Subje·cted to Torsion. • 641
v
· Venturi . TYl)e· Cowls and Engin~·.: lface11es Suita:ble for Multi- .
Engine Airplanes, Wind Tu1mel Tests of. • • . . . . • • 647
Vibration, Determinati on of. the. Elastic Axi's and Nat.ural · Per--
iods of Vibration of the Atlantic C-2A Monoplane Wing 645
:·I . • •• 1-'. .- w
Wheels, . Sta.tic Test. on the Materiel Division32 ·by 6Disc Wheel · 614
Wind Tmmel: · ·
Calibrat ion Constant- of Wri ght. Field Five-Foot Wind Tunnel 643
:.·. Wind Twmel Tests of: . .,
PH-413 Model Fitted with Various Fins and Rudders • • 603
1/20 Scale Model o:f:· the Materie:l Division Night Observation
Airplane • . . . . . . . . . . . . . . . . . . . . . • 610
1/ 24· Sca le-Model of the Douglas 0-2E..-1 Airplane Wing Cellule
Through 360 De grees. • . • . • • • • • . . • • . • . • 612
Venturi TYl)e Cowls and· Engine NaceJ.les Sui table · for .. Multi.:,.
Engine Airplanes . . . . • . . . • . • . • • . • • 647
Wing Cellule, · Wind ['u."1nel Te s-t of. 1/24 Scale· Model· .of the Douglas
0-2E-l Airplane Cellule Through 360 Degrees • 612
Wing: · · ·· - - ·
'rhe Calcula tion of. the· Natural. Frequency. of a Cantilever
Monoplane Wing • • • . • . • • • • • . • • • • • • • • 649
. l ' , : •. ••
Consolidated PIT'-3 Airplane. Wing Cellule in High ana Low .
Incidence. . . . . . . . . . . . . . . . . . . . . . . 626
Determination of. the Ela stic. Axis and Natural Periods ·of
Vibration of the Atlantic C-24\. Monoplane Wing . • • 645
Flutter Investi gation .of . :Bra dy's. Wind Tunnel"'.: Model .• ;. ·~ 608
Handley Page, Resume of Investigations :Made on Handley Page
Sl ots and Flaps. . • . • . . . . . • . • . • . . '. . . . . . . • . . . . . • 639
Some ASj)ects of Torsion in Multi spar Cantilever Wings. ~ 627
Static Test and Determination of the Elastic Axis of the
(Materiel Division) Improved Stressed Skin: TYJ?e Glider
- 6 -
• • • • 646
U-1003,A.C., 1/15/ 31
Wing •. . . . . . . . . .
""'t. , • • ~
. Wing (Cont t d):
Sta.tic Test of t:1e' i~is 2.:3 ·Expe..:-timental Three·_.Spar Mon; plane- ·
I nformation
Ci rcul a r No •
Wing St ructure J3i;.i.lt by the Keystone Aircraft Co:tpcration 617
Static Test of t Tie Xru ....:3·:;ExperimerJtaJ. ·Two-Spar Witlg Struc-ture
J3uil t by the .P~ eyst otie .Aire r-aft c·orporation. • • • • • 616
• • A ~ ·
·~ . . . . . . . . . 653
: 1 . • ·.
Study of Pressure .Distribution pa ta_ •••
' ! :::·,
. . 604
'i ·.'.·":· - ._.
Study . of. . \Ur~ g :B,],utter. Pt •. -~~ : .. ? ·est ~t _Appa:;-_~h~.s and Discu~sion
. "of "l?r6cedn1 e ; . . ". . . . . . . . . . . . . . . . . . . . 635
;,•.
' '.
• .I,
: ..
, .
.. .
·.':
... ... , .... .
. . r ,
·-
;_.; ._.
' :·
, .. . ( .
'.
• • > .·.
:- .·.
. '
U-1003,A.C., 1/15/ 31
NUMERICAL LIST
Title of circular and Air Corns Libr~ry Fil~ . No.
:·Nol ",: . . . . '·
;v: 601 ·':Flood· Li ght; A-:--2 and A-3, Handbook of Instruct'ions for Airdrome
D 13.46/ 89 .. .. . · ··. ·": : .· .
- -- .. , , · .. , .. ! ...... ' • ~.
• ••• .>,. . ...
• · 602' · 1£L:ndi:.:1g. Gears, ·, J)etermination of Stresses · in Lafidilig Gears and Design
of Shock Absorbing Units D 52.5/31 · ·
603
• • ~ • I I
Wind Tuhnel Tes ts of DH_:~· lfodel Fitted· ~i th Various Fins and Rudders
· D 52 .. 1 · D.H.4/ll8 .· •'
.:' .
.... ·. · ·: ·604- · Study-.'of Pressur~ -Dis~ '.:1:i ?'t~i ~~ D,=tta _ •• D 52. 33/l ~
605
•• J .
Determination ~f·C~nte~ of .Gravity'a rid· Mean Aerody11amic Chord
D-52.1/ 241
606 Handbook of Instructions for Airdrome Landing Field Flood Lights,
Ty-pe A-4 D 13.46/23
607 The Induced Drag of Any Biplane D 52.151/59
608 Wing Flutter Iaves ti gation or. Brady's Wind Tun:1el Model . D 52.33/276.
609 Effect of Cellule Arrangeuent on t l1e Rate of Autorotation by the
Strip Method D 52.151/55
610 Observation, Wind Tunnel Test of 1/20 Scale Model of tl1e Materiel
Division Ni ght Observation Airplane •• D~2.151/58
611 Aircraft I gnition, Recent Developments D 52 . 413/46
612 V/ind Tunnel Test of 1/ 24 Scale Mod.el of the Dougl as 0-2E-l Airplane
Wing Cellule through 360 Degrees D 52 .1 Douglas/ 12
613 Airplane Spi nning Characteristics D 52.151/65
614 Static Test on t he Ma teriel Division 32 by 6 Disc Wheel D 52 . 56/32
615 Study of Horizontal Tail Surfaces of Cons olidated XPT-3(NY-l)
D 52.1 Consolidated/5
616 Sta tic Test of the XHB-3 Experime:ntal Two-Spar Wing St ructure ::Suil t
by the Keystone Aircraft Corporation D 52.1 Keystone/3
617 Sta tic Test of the XHB-3 Expe rimental Three-S ~9a r llonoplane Wing
Structure l3uilt by the Keystone Aircraft Corporatfon D 52 .33/26
618 Study of Fatigue of Metal Pr opellers _Caused by Engine Impulses and
Vibration, Prelimi11ary D 52.43/450
619
620
Full Scale Tests of Semi-Ri gid Airship RS-1 D 52. 72/64
T'ne ComJ?uta ti on of Truss Deflections by the Method of Elas tic Wei ghts
D 52.39/ 7
- 8 - U-1003,A.C.,l/15/31
No.
621 Design of. 111russed Meta'l Spars .for Single 13ay Airplanes D 5'E;. 331/ 68
622 Te.sts on 6t Inch 11ietal Spars .'D 52 . 331/16
623 Flood-Light Test at Fairfield Air Depot - 1927 D 00.12/122/No. 2896
624 Precise Formulas for Restrained .:Seam with .Axial Load of Compression,
and with One . Restraining Moment Known n · o0.12/122/No. 2899
625 DetermL:1a t i on of Stability from Fl-1ght . ~est Stick For.ce. Data
D_ 52 .32/ 4
" ·. ..
626 . :c.oxisolid.a ted PT-"3 Airplane Wing Cellule .:.i n High and. Low I ncidence.
D 52.1 Consolidated/8
-627 : Some As~ects _of. To~sioi;i. fn Multispar -_ca.n~ilev:er ~Hngs .
D 00 .12/ 122/No . 2913 - - ·- . ·
628 Determfrl:a.ti•on. of tlie 'Rate·s of -Descent 6'f a Fallirig :Ma:ri and :of a
Parachute Test Weight D 00 .12/122/No. 2916 · ·
629 ._ Determinatio1i o:f "Structura:.l .Afrpl ane- Drag D. 0~ .1 2/~22/No . -2919. . ,
630 Dynarnometer Carburetion Runs on Curtiss GV-1570 Engines
D 00.12/ 1 22/No . , 2918~ .. -
631 Revised Nomographic Column Charts wi th Isobars of Wei ght and Tensile
Strength D 00.12/122/ 2922 - :: ·- · · ·-'
632 Comparison of Wind Tunnel Tests with Flight Tests on a Number of De­.
tachable :Blade Propellers Made F~oni the Same .Plari FoI'lll. n :00 .12/122
No . 2943 .
633 .Analysis of .Ai.l'.-.craf.t •.Accidents · D 00.43/U .·s .fl
634 ·Appli·cation of the· Leas t Work Me:tho.d · to .t l1e Eva l uat i on of Init·: al and
Temperature St:resses D '.00. 12/122/ lfo. · 299.8 ·
6:35 Study· of Wing Flt:tt t er:-'.Pt. 1 ! . D 00.12/122/lfo. 3002:. ·
636 ·s tatic Test Rei')ort ·of .Ty-pe E-1 ·.Airpl arie S2.d . ·D 00 .12/122/No .. 3005 .
. . . - .. ... -
637 Supplementary Report on Tests of ~ Inch Metal Spars D 00 .12/122/No .
2990. :
638 Test of Standard Water-C ooled Liberty-12 Engine with Various Pist on
Rings and Arrangements D 00 .12/122/No . 3006 .
639 Resume of Investigati ons Made on Handley Pa ge Slots and Flaps
D 00.12/122/No. 3020 .
640 Relationship of Laboratory Tests and Cold Weatl1er Motor Operation of
Various Oils - Part II D 00 .12/122/ No . 3058.
641 The .All owable Stress in Tubes Subjected to Torsion. D 00 .12/122/
No . 3070
- g· ;... U-1003,A.C., 1/15/ 31
No.
642 Rigidity and Fle~ibility of Airplane Structures D 00.12/122/No. 30~4
643 Calibration Constant of Wrii;nt Field Fiv·e-Foot Wind Tunnel.
~ 00 .12/122/No. 3082. ,• -
644 Miscellaneous Collected Airulane Structural Design Data Formulas
and Methods · D 00.12/122/No~ 3083 ·
645 Determination of the Elastic Axis and Natural Periods of Vibration of
the Atlantic C-2A ionoplane Wing D 00.12/i22/No. 3097
646 Static Test and Determination of the Elastic Axis of the (Materiel
Di vision) I mproved s·tress·ed 'Skin TY.Pe Glider · Wing D 00 .12/122/No. 3099
647 Wind Tunnel Tests .. of Venturi Type Covils and .Engine Nacelles Sui table
for Multi-Engine Airplanes D 00.12/122/No. 3133
648 Instructions for Assembly of Detachable Blade Propellers
D 00.12/122/No. 3169 '
649 The Calcula ti.on of the Natural Frequency of a Ca~1tilever Monoplane
Wing D 00.12/122/No. 3173
650 Proposed Method of Determining Design Tail Loads for· Airplanes
D 00 .12/122/No. 3148
651 Physical Characteristics of Paracl1Ute Clo-th under Varying Atmospheric
Conditions D 00.12/122/No. 3228
652 Statistical Studies ·of Aircraft Accidents and Force·d Landings
J3 70/U.S . /32
653 Study of Wing Flutter Part II. ·D 00.12/122/rfo·. 3237
654 Millivolt-Temperature Relation of . the· Standard Air Corps Iron­Constantin
Thermocouple· ·n 00 .12/122/No . 3280
655 Airplane Do~es, Doping and· Dope Room· Requirements D 00 .12/ 122/No . 3290
656 Test of Armstrong-Whitworth Ste.el Si:lars under Combined Axial and
Transverse Loading D 00,. 12/122/No.- 3296 .
657 The McCollum-Peters Six Element Telemeter Strain Gauge Set
D 00.12/ 122/No.3313 .
- 10 U-1003,A.C.,l/15/31