NASA NACA-ARR-3E25-1943 Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane《P-47B飞机尾翼上压力分布的全面风洞研究》.pdf

《NASA NACA-ARR-3E25-1943 Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane《P-47B飞机尾翼上压力分布的全面风洞研究》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-ARR-3E25-1943 Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane《P-47B飞机尾翼上压力分布的全面风洞研究》.pdf（39页珍藏版）》请在麦多课文档分享上搜索。

1、.bI.ili.if!i/-.,6NIAYM 1947 ,. ; ./,.7-.-. ,-, *. . . - -* - ARRNo. -W25NATIONAL ADVISORYC“+-=( positive when left wingmoves forwzrd8 control-suraae deflection, degrees; positive withelevator down or rudder leftc downwash ane at tail measured relative tofree-stream d!$QtLon, degreesit angle of st%Q3

2、15.zersettin with resect to thethrust axi,edge downP mass density 05Subscripts:o free streama stabilizere elevatorf fLZr ruddert horizontal tailis isolated taildegrees; psitive wih trailingairs slugs per cubic footsurfaceAPPARATUS AND TESTSThe Republic P-.47Bis a high-altitude pursuit airplane(figs,

3、 1 and 2) weighing about 13,500 pounds and equipdwith a Pratt gr the rudder: . Thestabilizer incidence for the tests was 12 and the Ieadingedge of the fin was offset 1 left from the longitudinal axisof the airplane.A total of 437 flush-type orifices was installed in theempelmage as follows: 40 2n th

4、e stabilizer, 150 in theelevator, 68 in the fin, ad 79 in the rudder. The orificelocations and rib dimensiQn9 are given in figures 5 and 4and in tables I, II, and 111.All tests were made with the propeller removed. Atzero angle of yaw and at airplane angles of attack of 0 and15,6, the tail-surface p

5、ressures were measured for several angular deflections of the elevator. (See table IV.)Similar tests were made for a range of rudder deflections atyaw angles from 0 to 9; One test at an intermediate angleof attack of 5.1 and several tests at an angle of attackjust above the stall (17.1 were also mad

6、e.The elevator was deflected 3 for the rudder tests.:Td :evator -d rudder tabs were locked at settings of -2respectively. The thrust axis, the stabilizer chord,and th longitudinal axis of the airplane were used as refer-ence lines from which angle of attack, elevator deflection,and rudder deflection

7、 were measured.The tunnel airsneed for the tests at the two low anles.of attack was 87 miles per hour. The testsangles of attack were made at an airspeed ofRESUZTS AND DISCUSSION .at the two fiigh63 miles per hour.Isometric charts of typical pressure distributions overthe P-47B tail surfaces at thre

8、e angles of attack for differentcontrol-surface settings and yaw angles are shown id figures 5to 15. I$o unusual tail load distributions are indicated bythese results. Por high angles of attack of the fixed sur-faces theexpected peak loads occlm on the leading edge of ,the fixed surface, and for lar

9、ge deflections of the movablesurfaces the expected peak loads occur near the hinge line.A peak load occurs on the elevator mais balance for elevatorangles in which the nose of the balance .pro”ects appreciablybeyond the stabilizer surface. i(See fig., .).,.b.,-Provided by IHSNot for ResaleNo reprodu

10、ction or networking permitted without license from IHS-,-,-5A reduction in normal force on the ribs adjacent to thefuselage is clearly shown by the data. This reduction innormal fcrce which increases with angle of attack, resultsfrom the wake of the fuselage and wing-fuselage juncture.(see figs, 5 t

11、o 8.) A large reduction in the pressure peaksat the right side of the horizontal tail surface was measuredatq= 17*1O (fig. ). The decrease is dueto localstalling which occurred14012:4-610418ao1-2. .4.G-.-:11 .it+2127.0 .,.1$!3$%.:$.l% ag.:2%. ,“ 3339Rlb1;i ., - . .,.,.-.,-. .2, 9. ,. . .3, 8. . .,.

12、,. ., i.,-. .,k,7. , .a71.;,6-;. b,:-.-ZlevatorTube.-%., :,1”.: 5,.12.6,137*4.8,15.9,1610,171718,2519,2620,a, 28=s 29.,23,-30.4,31“17m, 25.19; 2620, 2-7 :21, 28 2?,29t23,3024,31.17 i8,25.,XL,26,20, 27ti;5822,29 ,23,30.4, 31.f,.17.18,25 “.19,26 ,20,27.-,.21,.8 “. .22,29.2$ 3924,31NACA0, -. .Provided

13、by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-m NACA-1%I,._RibFlnTubeTASU IICHORWISE XJXATIOHS OF VERTIOAGTAIL ORIFICESnli?13. ”*,15”.- -1, 32, 40I, a2, 93,104,115,1.26,137,401, 82,93,10b,ll5,126.137* 401, 92, 103,114,125,13,6, 47, 158, 1601, 92, 103, 11l!,

14、 125,136,47, 158, 16Static.nain h. from leadlng edgeStation113401;359131821o14591521+27$o-$3584228330246111$2$3$4$.-RlbU1213415.6- - -y- ?7-,.- 7 .- -YV., -, . . . ,-, . ”,. . ., .:RudderTube56,107,118, 129,13156,2217, ”2318, 35; 18? 335, 6 58 40 -u? 111 31; 16 i 3:612 35 23* 11 513 4% + 4; 514 54 3

15、5 18 515 74 47; ,21+ 516 26 - 21 5-. .-lDimensions given are from hinge line totrailing edge.“Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1r15TABLE IVNORMAL-FURCE COEFFICIENTS 10-533;33;33333;-5-15-203333333333333333333CNS-0.057.001.176-.168-.-.0

16、17.010a71 022.031.028.0100003.030.01.20i.564.67.472.289:2;.629.655.671.654;lig.729.634:?Z.639.670.661.664.78.77!/c745,750Ne0.007.136.34Ii-017.1290115.116,111.125.137.126,14.123.11.11I.118.178.3.30.264.004:f?:.229.226.223,232.180.225.225.217a71227.229.226.222.219.236:%9.29.26!.263-mfk-0003-.06-.091-.

17、071.000-0109-.156-.222,136.092.284a71 202.180.46a7137z.274-.020a71 002.043.035.032-.010.016-.039-.073Ii:1;-.201.107.057.007.211046,09.31z.204;122.008.299a222.167cr0.023.008.018-,002.093-a71 053:;7a71 02ii-.032.069-.035-.109.059-.072-.166.010.Q27a71 o,022.026.022a71 009-.ok7-.103-.200-.268-:1:1-“07-.

18、121.05-.01k-.14,085-.01i-.10a71 047,057-.053-.158. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,., i. !1.t,1 iJ,i.t , .“ ,L.-, 1L-439,Fre 1.- The P-47B airplanemounted inthefull-scaletunnel.wProvided by IHSNot for ResaleNo reproduction or networ

19、king permitted without license from IHS-,-,-#. L-439,.,.,i.,;,.,.i,:.,.3!,/,.f,.,. .,.:-1“1:.,;,/.,Aretx, 6qftr/49- Mi?g 300 .J%Wicer :;6E/ewtor )Q. . . E/emtir L 36 dF/h /360A%dder”) /2,90. . . -wiv (1tfigure 2.- 7%me-Hkvv dhwtng of he P- 47B ul+lone.Provided by IHSNot for ResaleNo reproduction or

20、networking permitted without license from IHS-,-,-.-IWCA-.Q.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-“ .3/ oFig. 4PAS f #loA% 447A7jpe *).- Chonzkise/acafIbrM0/ AorIzonfd-fffi/w4%es,.Q.Provided by IHSNot for ResaleNo reproduction or networking

21、 permitted without license from IHS-,-,-NACA AFAxFis”5“,. .pressure dZn+ibufion. I L. -yfoToO*flpper swfice_ Lower 5udQce#,9 :.,*rt I50!AProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .NACAflpper surfbce_ 1 Lowef wffuce._ Opper wrhce _ L owePatfpf

22、aceProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. .NACA./re 9- - J.,.!,./ .,1,2.9(Wd0. 0- 0.- 0. 66e gr(d;d (g)o50-15 030300 50 100Dstahce outboard from fhselage ceriter llne,in.Figure 17.- Stabilizer epan loadinge,uP5”6”Provided by IHSNot for Res

23、aleNo reproduction or networking permitted without license from IHS-,-,-,:i. ,“!,“,1,.j. III,-1.0Cnco1.0+ IRight sido -. i,/ / - ,-1 k,I . 0 1ii :! / /#I / T/ ii ! I1 Y . 1 8:= - “. .-.“.*(deg)0. 0- c)Distance outboard from fuselage center lime, in.Figure18.- Elevator span loadings,aT,15.60. “6r(I.,

24、.,i,., ,.,.,.,:,I.,1-1,.:,.,+,I.,i.,.,!.,.1.-. I _.-CnCI1.0 iii- ._.02,0- , /-%. .: -. /10 50 100Distance outboard from fuselage center3igure19.- Horizontal-tail span loadings,fi,15.60.,$(deg)u. 0-. -. 0.- 0- 6line, in.,tie. ilr(deg) (deg)005 0-15 03 030,.Provided by IHSNot for ResaleNo reproduction

25、 or networking permitted without license from IHS-,-,-itAc4.Figs. 20,21o“Zirl8 .4 0 -4 Cnc/fIl :,*I*. .i r 1/3igure20.- i?inand rudder span loadings,mT,15,6.Iigbre 21, - Vertioal-il span“ loadings,15.5,.Key fpr both fre8$ 8e 6r(ed (deg).(deg)030o 3 .3. -0 3.-9”a6 3 -3Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-