NASA NACA-RM-A8E03-1948 Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel II - the effectiveness and hinge moments of a constant-chord plain fla.pdf

1、copy No. 113 RM No ME03 RESEARCH MEMORANDUM- TESTS OF A TRIANGULAR WING OF ASPECT RATIO 2 IN THE AMES L2-FOOT PRESSURE WIND TUNNEL. II - THE EFFECTIVENESS AND HINGE MOMENTS OF A NAT CONSTANT-CHORD PLAIN FLAP By Jack D. Stephenson and Arthur R. Amuedo Ames Aeronautical Laboratory . Moffett Field, Cal

2、if. , .-.:. _ i.r. _ =, y ; . i IONAL AD;lSORY COMMITTEE FOR AERONAUTICS - I WASHIN TON September 9 1, 1948 .- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Distribution 18UA/8mcurity Clasificatiorl Offfear uthotity t0 Deccfasaify NACUNASA Doaunmtr

3、 Datad Prior to Januuy 1, 1960 gffrctive thfa date, all mataridlalrrrificd bv this Center prfor ta January 1, 196Ur it dealaasifiad. Thin action doer not include material drriv . . . . l Dtclanmifitd by authority of LaE Btcutity Classification Offfcer (sco) lttttr dtttd Junt 16, 1903,= rt-marking. a

4、nd eht signature of ptreon gmrfotaing the rf re-maxking a hrgt anewquaze chordof the flapaft ofthehgnge line,feet dynamic pressure ( e , pounds per square foot epanwise station, feet ooefficient of tieoosfty of air, slugs per foot-second mass density of air, slugs per oubic foot The tests desuribed

5、in this report were conducted in the Ames afoot preesure tunnel, which fs a varlable4ensity wIndtunnel having a circular test section edified by the addition Of four equally spaoed flat section8 of Afoot chord. The oharacteristio8 and perform8m e of the wind tunnel are disoueeed in reference 2. Prov

6、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARMNo.A8EC3 The semiepan triangular wing, which was constructed of steel, was mounted on a turntable in the flat section on the tunnel floor. The unmodified wing had 5percent-thiok, uncambered, double-we

7、dge sections with the maximum thicknese at 20 percent of the chord. A limited amount of data was obtained with the leading edge shsrp and the ridge line (line of nmcdmum thiotiess) sharp, and with the leading edge sharp and the ridge line rounded to a radius of 32.22 peroent of the chord. The major

8、portion of the data was obtained with the ridge line rounded to a radius of 32.22 peruent and the leading edge ,rounded to a radius of 0.25 percent of the chord. Figure 1 shows the dimensions corresponding to the three profiles. Figures 2 and 3 are photographa of the model in the test section illust

9、rating these modifioations. Dimensional constants used in defining the coeffioiente for the Mel are given in table I. A wing-body oonibination was formed by the addition of half of a body of revolution, munted sgmmetrioally on the wing, as shown in figure 4. The coordinates of the body are also show

10、n in this figure. A oonstantihord flap having an area aft of the hinge line of 1.8 squsre feet (20 peraent of the original unmodified wing area) was supported on three hinges and restrained from rotation at the inboard end by an eleotric straiwge unit and an angle-indexing bracket. (See fig. 2.) The

11、 flaphadaradius nosewithno aerodynamio balanoe and an unsealed nose gap of 0.028 izh (0.37 gerwen-t of the flap chord). Flap angles in increments of 2 from 30 to -30 could be set by mans of the indexing bracket. In tests of the wing-body oombination, the flap extended into the fuselage through a cov

12、er plate which was ohanged for each flap setting. It was necessary to leave clearance in the plates to allow for the deflection of the flap due to the aerodynamic load. These gaps averaged about fiv-ighths inch in width at the trailing edge and tapered to a small olearance at-the hinge line. The gap

13、 between the wing root and test-section floor was between 0.01 and 0.15 inch where the wing root extended beyond the turntable; consequently, some air leekage was possible. The boundary layer on the tunnel floor, the displacement thickness of whioh was 0.5 inch at the model, was not removed. CORRECT

14、IONS TO DATA . Corrections have been applied to the data to acoount for the effects of tunnel-wall interference, constriction of the air stream, tare forces on the model-support plate, and distortion of the flap . 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license

15、 from IHS-,-,-. - . . EACA RM No. A ,892 .918 0933 .912 q, corrected a. uncorrected Tare Corrections Wing alone 1 .ooo 1.000 1.000 1.000 1.004 1.006 1.009 1.013 1.017 1.000 1.008 1.010 1.012 1.018 1.024 1.034 1.043 1.052 Tare correctiona were applied to account for the turntable drag but not for aer

16、odynamic interference between the mdel and the turn- table. The tare4rag coefficients were found to vary with Reynolds nlmiber only. The values are a8 follows: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 NACARM Tam-drag coefficient Reynolds nu

17、whereas the chsngesinliftalld pitchiwment coefficients were relatively small. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 RACA RM IVo. Adrag ratio with lift coeffioient for the winwhloh oocurred at a lift coefficient of about 0.2, were never g

18、reater than ll. W!emfile Modifications Figures 25 through 28 indicate the ae rodynamic effects of 8lTghtl.y modifying the wing profile. Cwes presented in these figures are uncorrected for flap distortion, the effect of which was investigated only for thewingwdtharoundedleadingedge aroundedridgelines

19、. In the investigation of the effects of-the modifications to the airfoil section, the wing was first tested with true double-wedge seut90ns and was subsequently tested with -MO alterations, rolllzded ridge line8, and a rounded leading edge with the rounded ridge lines; (See fig. I,) Effects of the

20、edification are noticeable only at the higher any far forward to obviate the need for irreversible controls, the large up-elevator angles required for level fl . . . . . . . . 3.93 ft Withsharpleadingedge 4 ft Wingsemiepm,b . . . . . . . . I. 3 f-b Root-meae-square chord of the flap, wingalone . . 0

21、.6107ft Wing and body 0.6043 ft I sYEi.lfaikZef ?t .“T i 3 f-b i Wil3BandbOdy . i.565 ft u . .- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. NACARMmO.A8EO3 Table II.- Aerotivnamii charac ferkffcs of a frianguf ar win Reynolds numbe S,3UCj 8 00;

22、wifh variou5 flap angles. Mach number, O-50. - . G cp a f.$f -.264 -.169 I:%5 .07 d 25 d :4 3 -.4x! -. 2x0 -.a6 -.lz!o 0.076 -050 .02d .016 .ood .m7 .oo % .Ol :%S .076 .lll 2% :% .6M, .420 .280 .I20 :3 .oll .Ol 22 :g -.lS -207 Z:Z -.=9 -.a37 -23. -.R s. -.m -.2s3 -2% - -.150 -.162 -a71 -.mg -.2m -.o

23、m 3: : 33 -378 .394 -.222 -242 IL% -.311 -.321 22 -.421 .OS .0= -031 .039 ;g i= . +-. I I I I I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18 Table IL-Concluded RACA EM No. A8EO3 a 0. 12 2 -. 10 -. sn 1:g -:% .ll.l :S 2% .Y=Y LO18 1.09s :2g :g5

24、.97 3 L.050 L.110 41% ,.ol2 ,076 :g72 328 :465 :g :872 s $2 2% 0.090 .059 :Z .OlO :Ei .Oll SE .09g .13 .ld 224 :% .430 fE $2: :Z; .013 .m9 .oog :g; .Opj 1% .I24 .167 .218 2 .4sl : “:o”Z -06s :% .024 .Oll -A4 I:$; 9074 -.ogg -.lOl -.lll -.120 1:% -.ool .090 :Z - -.9lO -.Sl -.70 a -.I8 ,207 c, 0.1 7 2

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26、“9; -.06t G ;:g 1:15g l.lll 1.07a -9m -631 :E5 :ZS :Zi: .xm ,115 -:“og -.162 -.a9 mm- - cm -0.a 1: -.19 -.20 -.2I -.20 1: -.17 -.l I:$ -.lO -.og 2% i;sj I:% -.l 1 2 22f -.112 :g -.070 -.a34 -.176 a- - - . -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IH

27、S-,-,-20 s -4 -4 -4 a 28 2. 22 20 2 14 io2 a f 0 -2 -6 -is -10 i 2 -4 186 -10 G I.59 3.g .23 202 $ 3% .023 .012 .008 .m7 .OlO .020 :oOZ? .095 g; 32 .221 . iao .I33 :% .036 .020 ,011 .wa :Z :% 2 .O s .l 4 :ZZ 33 :Z 3 39 3 $3 .OlO .OlO .015 ;z .092 .129 Tub/e h!T.- C on; -.102 -.OBb -.070 -.020 -.006

28、.OlO .022 -.og2 27J :% - .OlO -.005 23 .o 3 t : :g I:2 a -.07 -.o$l 2; .Oll .o33 g .1og .132 I:fg -.lQ CzJ -.o43 -.027 -.012 :E 2 :% .oa1 .wg .120 -1 7 ? .I 2 -12 -12 -12 -12 -12 -12 -12 -12 -12 -12 -12 -12 -12 -I2 -E -E -12 -12 3 -6 -it 2 24 22 z 3 12 10 ; 2 2 -4 -6 -it 1% :5“ I :%6 .120 .160 1425

29、.2 a2 :2$ .l% :Z7 b -05 -041 :%Z f% .05S :ZI .149 .I95 .x11 .214 -0.100 I:% -.o46 -.029 -:t?f $ .o 1 ,068 5% ,122 :Z .I79 .1go :% .27a .293 ,080 .117 .092 .u5 .104 .116 .154 .I77 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM lb. A -IO 20 lb

30、 16 14 12 ? f 2 1; -I% .lOl .066 :o% .013 .006 23 .a26 .047 .075 -3a4 :Fi z 525 .a17 .Ol2 52 .021 :% .32Q -263 .a. .ld .115 -3.i sltt .020 :% .Ogs -.177 -.200 :g 1:; :g -.oa a -.o 9 ,029 -.ll1 -.102 -.106 -.o 9 2 -.o 2 -:%i .024 .037 :755 .QV 2 .llV ch f:fg -.1z“ z ?%J -.042 -.022 -.001 .016 .Q 5 :r

31、 .oa t r.012 :% u.276 :EG :g .675 :ZiZ :gz m.190 - .6oa .!32 .419 .3= 562 .o 9 a :4; 11% :fZZ - mm- - :oOS .wv .w9 .015 :% -074 -110 .272 .a .I 6 d :Z -012 .014 .OlS -100 .142 -250 .l 7 z .1 9 -111 :g : t 2 -020 .025 :TY .067 .080 .wa .115 .l ? .1 7 2; -:x .o 5 -032 :z .od 3 .100 .ll .12 i 2; 8 2; .

32、2la - :% :% .Obe - - - - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 NACA Bl No. A3; .106 .1?6 -.06a -.I3 -.020 .OOl .OPO 33 .07 .09 t .11 z 227 I, G -e - -%g 379 -.040 -.028 -2% .040 .o69 -.164 :lbl -.071 -:zi $3 .03 :$ .117 I%“ :pg -.012 .W

33、.032 :% .103 :3 0. log :“g -.a5 -.oO $7 f .O $ .o 2 .wo .I07 :32 Ag -.026 :1“ .2 :a .a75 ,050 .OP .ol3 .a9 .0%3 :“Z .llS 2% .ql .a6 .163 23 .oll .m2 .017 .a9 .04a .073 .=I. :Z :E .jJ -028 .m7 -.ola : a G .OlC ,092 :a ,670 ,912 -.797 z:2 -.14 9 -.06a .017 :% .270 G .I1 .lO 2 .102 3i .o a b $27 ii! a.

34、021 8.036 04a 2% 072 Od5 22 .l21 :% .wJ s$!z I!3 -.wl -.caa -a27 -.173 -.2.x- a -12 -10 :t 1: 0 : 6 8 10 ii -12 -10 -8 :t -2 0 : 6 li -0.723 -.603 -web :% -x72 -.m2 :% $2 .bz? 2% ,754 Al5 .019 :E!E :$i ,174 - IS .059 :E -.CK% -.QV Z$ -.068 -.Cg -.175 4x7 .we .I15 ;i$ .525 640 .l% .150 :Z :Z :Z .022

35、m2 JJ49 :$ .u7 .215 Iii :% 267 .ll9 .2bO .laZ :Z 2.2 :E :E Jo0 - :% .071 .045 5% J-JU :Z .097 :Ei 52 - a9 :Z ;g .017 -:zi -.032 11% -.m -mm . -.; 431 -.533 -430 -.338 I:% -.a69 .a3 .137 :% .bbo .553. :E 2: -.355 :$i$ -.c95 .W5 .lOC .210 .3m ,419 ,530 . . . . Provided by IHSNot for ResaleNo reproduct

36、ion or networking permitted without license from IHS-,-,-Hinge he, A L%hwsitms s&n in inches lmh?ss oihenuisr, noted. Sharp ridge, sharp LE. F&we A - Semispan mode/ of a trjangulat wing of aqwct rani? 2 hsted h/he Ames l2-wpi?swi? whdtlmd I . . !f! F ks k 6 W Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-