NASA-TN-D-2180-1964 Aerodynamic data on a large semispan tilting wing with 0 6-diameter chord fowler flap and single propeller rotating up at tip《带有0 6直径弦 福勒襟翼和在末端旋转的单螺旋浆大半翼展偏转机翼的空.pdf

《NASA-TN-D-2180-1964 Aerodynamic data on a large semispan tilting wing with 0 6-diameter chord fowler flap and single propeller rotating up at tip《带有0 6直径弦 福勒襟翼和在末端旋转的单螺旋浆大半翼展偏转机翼的空.pdf》由会员分享，可在线阅读，更多相关《NASA-TN-D-2180-1964 Aerodynamic data on a large semispan tilting wing with 0 6-diameter chord fowler flap and single propeller rotating up at tip《带有0 6直径弦 福勒襟翼和在末端旋转的单螺旋浆大半翼展偏转机翼的空.pdf（156页珍藏版）》请在麦多课文档分享上搜索。

1、NASA TN D-2180 e./ - - NASA TECHNICAL NOTE 0 AERODYNAMIC DATA ON A LARGE SEMISPAN TILTING WING WITH 0.6-DIAMETER CHORD, FOWLER FLAP, AND SINGLE PROPELLER ROTATING UP AT TIP by Murvin P. Fink, Robert G. Mitchell, und Lucy C. White Lungley Reseurch Center Langley Stution, Humpton, Vu. NATIONAL AERONAU

2、TICS AND SPACE ADMINISTRATION WASHINGTON, D. C. FEBRUARY 1964 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECH LIBRARY KAFB. NM 015433b AERODYNAMIC DATA ON A LARGE SEMISPAN TILTING WING WITH 0.6-DIAMETER CHORD, FOWLER FLAP, AND SINGLE PROPELLER R

3、OTATING UP AT TIP By Marvin P. Fink, Robert G. Mitchell, and Lucy C. White Langley Research Center Langley Station, Hampton, Va. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230 - Price $3.00 Provided by IHSNot

4、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-AERODYNAMIC DATA ON A LARGE SEMISPAN TILTING WING WITH 0.6-DIAMETER CHORD, FOWLER FLAP, AND SINGLE PROPELLER ROTATING UP AT TIP By Marvin P. Fink, Robert G. Mitchell, and Lucy C. White SUMMARY An investigation has been m

5、ade in the Langley full-scale tunnel to determine the longitudinal aerodynamic characteristics of a large-scale semispan V/STOL tilt-wing configuration having a single propeller which rotated in such a direc- tion that the propeller blades rotated upward at the wing tip and downward near the root. T

6、he wing had a chord of 0.6 propeller diameter, a Fowler flap, an aspect ratio of 4.05 (2.025 for the semispan), a taper ratio of 1.0, and an NACA 4415 airfoil section. The data are presented without detailed analysis, but three results were found to stand out very markedly from a casual inspection o

7、f the data. First, the tuft tests showed no stall on the part of the wing immersed in the propeller slipstream at angles of attack well above that corresponding to the peak of the lift curve for the high-thrust conditions corresponding to operation in the STOL range of flight. Second, the wing-flap

8、combination was found to be sufficiently effective to prevent wing stall except in the unprotected center section (judged from tuft-test results) over the entire range of STOL operating conditions cov- ered in the tests, which included the conditions required for descent angles as high as about 20 f

9、or each test. And, third, the use of leading-edge high-lift, or stall-control devices was not found to be beneficial in the conditions corre- sponding to the STOL flight range, evidently because the wing did not stall with- out such devices. INTRODUCTION Most of the aerodynamic research that has bee

10、n done on the tilt-wing propeller-driven V/STOL configuration in the past has been of an exploratory character and has been obtained with small-scale models. The interest in this type of airplane has now become so substantial, however, that there is a need for large-scale systematic aerodynamic desi

11、gn data for this type of airplane. A pro- gram has therefore been inaugurated at the Langley Research Center to provide such information by means of tests of a large-scale semispan tilt-wing-and- propeller model in the Langley full-scale tunnel. Tests have been completed on a model having a single p

12、ropeller on the semispan wing and having a chord-diameter Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ratio of 0.6, a 40-percent-chord Fowler flap, and three different leading-edge flow-control devices - a slat, a droop nose, and a Krueger flap.

13、The investiga- tion covered a range of angle of attack from -200 to goo and a range of power conditions from zero thrust to that required for hovering. The direction of pro- peller rotation was such that the blades were going upward at the wing tip. The lift, drag, and pitching moments of the model

14、were measured over the range of test conditions and the flow was observed by means of tufts on the upper surface of the wing. The results of this investigation are presented herein without detailed analysis in order to expedite their dissemination to industry and the military services. A few observa

15、tions are made, however, of some of the more obvious results. SYMBOLS The positive sense of forces, moments, and angles is shown in figure 1. The pitching-moment coefficients are presented with reference to the wing quarter- chord line. The coefficients are based on the dynamic pressure in the prope

16、ller slipstream. Conventional coefficients based on the free-stream dynapic pressure can be obtained by dividing the slipstream coefficients by (1 - CT,); for example, CL = cL,s/(l - cT,s)* The coefficients and symbols used in this paper are defined as follows: CL CL, s cD, s Cm, s T, s b C 2 lift c

17、oefficient based on free airstream, qs L lift coefficient based on slipstream, - qSS D drag coefficient based on slipstream, - qSS MY qssc pitching moment based on slipstream, - T thrust coefficient based on slipstream, fir? 9s 4 propeller blade chord wing chord, ft Provided by IHSNot for ResaleNo r

18、eproduction or networking permitted without license from IHS-,-,-D h L MY 9 r R S T a 6f 6s s, s, P V propeller diameter, ft; also, total model drag, lb width of slat or of flap-slot gap; also thichess of propeller blade total model lift, lb pitching moment, ft-lb free-stream Wamic pressure, - ”*, l

19、b/sq ft 2 T slipstream w h/c = 0.024; h/c = 0.012; h/c = 0.024; at: 6s = 200 6s = 200 6s = 30 6s = 30 Flap deflection, deg 6f = 0 6f = 20 6f = 40 6f = 50 6f = 60 6f = 60 * 6f = 40 6f = 50 6f = 50 6f = 50 6f = 40 6f = 20 6f = 50 6f = 50 6f = 50 6f = 50. 6f = 50 6f = 50 6f = 50 6f = 50 Table 1 2 3 4 5

20、 6 7 8 9 10 11 12 13 14 15 16 17 19 20 la Figure 10 11 12 13 14 20 21 22 23 * Alternate hinge point. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-The tests were made over a range of thrust coefficient from 0 to 1.0, and for any given test the th

21、rust coefficient was held constant over the angle-of-attack range by adjusting the propeller speed to give the required thrust at each angle of attack. angle required for zero lift to that required to stall the wing or develop a drag-lift ratio of about 0.3, whichever was lower, except for static th

22、rust case) where the angle-of-attack range was Oo to goo. The angle-of-attack range for the tests was approximately from the CT, = 1.0 (the The data presented have not been analyzed in detail but have been examined First, the tuft tests showed no stall on the part of the wing immersed to observe the

23、 general trends. From this examination, three results are note- worthy. in the propeller slipstream at angles of attack well above that corresponding to the peak of the lift curve for the high-thrust conditions corresponding to opera- tion in the STOL range of flight; however, for the low thrust coe

24、fficients, the center-section stall correlates with the angle of attack for maximum lift. Sec- ond, the wing-flap combination was found to be sufficiently effective to prevent wing stall (judged from tuft-test results) over the entire range of STOL operating conditions covered in the tests, which in

25、cluded the conditions required for descent angles as high as about 20 for each test. edge high-lift, or stall-control devices, was not found to be beneficial in the conditions corresponding to the STOL flight range, evidently because the wing did not stall without such devices. Third, the use of lea

26、ding- Langley Research Center, National Aeronautics and Space Administration, Langley Station, Hampton, Va., October 18, 1963. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 1.- TAHTIATED AERODYNAMIC W FOR 6f = Oo, 41 = 0 a, de.s -20 -15 -10

27、 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 90 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 I r I 7 a, deg -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 -20 -15 -10 -5 0 5 10 15 20 25 m 35 40 45 50 -20 -15 -10 -

28、5 0 5 10 15 20 25 30 35 40 -20 -15 -10 -5 0 5 10 15 20 25 m 35 cL,s 1 cD,s I %,s crp,s = 0.80 -0.514 -.348 -.148 .042 .240 .437 .644 .825 .954 1.059 1.173 1.249 1.300 1.328 1.339 1.317 1.203 -0.057 -.067 -.056 -.047 -.Oh -.023 -.Om -.020 -e039 -.059 -.077 -.094 - .lo5 - .113 -.112 -.111 - .lo1 -0.70

29、4 -. 771 - .814 - .825 -.eo5 -.769 - .713 -.639 -.5m -.w - .267 - .123 .017 .155 .276 .393 .w -0.w2 .w3 -.002 -.003 .w1 -.007 - .Ol9 crp,s = 0.60 -0.669 -.475 - .229 .016 .558 1.096 .284 .852 1.215 1.317 1.430 1.443 1.481 1.455 1.419 -0.448 -.531 -.%8 -.596 -.w -.5G -.464 -.377 - .243 - .lo7 .069 .2

30、34 .379 .488 .5% -0.066 -.075 -.&3 -.074 -.063 - .058 - .Ob5 - .053 -.O& - .lo5 - .142 - .164 -.1e0 - .184 - .189 crp,s = 0.95 -0.928 -.%4 -.984 -.%1 -.976 -.956 - .916 -368 - .789 - .727 - .628 - .544 - .454 -.348 -.237 - .lo8 .002 .l32 .250 .374 -0.374 - .253 -.ll5 .021 ,167 .296 .540 .663 .749 .8

31、27 .905 .964 1.022 1.060 1.109 1.126 1.135 1.140 1.125 .428 -0.048 - .036 - .026 - ,019 - .011 - .007 - .003 -.w4 -.O& -.014 - .014 - .018 - .026 -.030 -.om - .024 - .026 - .023 - .017 - .010 cT,s = 0.30 -0.765 -.6u -.306 0 .350 .TOO 1.076 1.401 1.516 1.617 1.651 1.598 1.488 -0:070 -.a5 - .270 -.82

32、- .273 - .214 -.122 -.016 .152 .328 .505 .37 .776 -0.053 -.llO -.115 -.097 -.083 - .072 -.a5 -.loo -.la -.a5 - .259 -.273 - .275 CT, = 0.90 -0.434 - .284 -.U6 ,040 .207 .363 .524 .6% .777 .882 .977 1.061 1.120 1.167 1.180 1.189 1.191 1.169 1.145 -0.852 -.905 -.933 - .941 - .924 -.e% - .852 -.789 -.6

33、% -.6ca - ,493 - .384 - .265 - .142 -.OS .&9 .zoo .297 .379 -0.048 - .Ob3 -.034 - .026 - .010 -.Oll -0.881 - .718 -.351 .a .4m .a28 1.289 1.661 1.828 1.976 1.783 1.679 .003 - .021 -.016 0.264 . u.5 .027 .025 .047 .OW .194 .3% .527 .7= .a75 1.031 -0.049 -.128 - .141 -.115 -.OW -.0q2 -.u.6 -.139 - .22

34、2 -.r13 -.3m - .382 -.035 -.047 -.OW - .057 - .063 - ,074 - .071 - .071 -e059 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Ill 1ll1111111lllI Ill I u-, = u- Cm,s -0.238 - .250 - .256 - .245 -.246 - .252 - .260 - .269 - .283 - .282 - .284 - .270

35、-. 255 - ,233 - .263 - ,203 - -0,267 - ,316 - .321 -.3a - ,326 -.j46 - ,366 -. 370 -.385 - .381 - .370 - .352 -0.276 - .365 - .392 - .398 - ,421 - ,455 - ,479 - ,490 - ,496 - ,532 -0.310 - .432 -.469 -.474 - .499 - .547 - .579 - .596 - .628 - .632 a, deg -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50

36、 55 -0.762 - .799 -.79 -.775 - .725 - .654 - ,557 - .445 - .316 ,069 .398 - .183 - .058 .194 .305 .476 -0.178 .024 .432 .649 .851 1.055 1.274 1.321 1.390 1.405 1.410 1.388 1.360 1.315 .238 1.213 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 90 = 0.60 -0.246 -0.496 - .019 -.580 -.57

37、2 - ,543 -.487 - .386 1.450 - ,273 1.662 - ,135 1.658 ,017 1.675 ,180 1.630 ,321 1.599 .450 cT,s = 0.30 -20 -15 -10 -5 0 5 10 15 20 25 30 35 CT, = 0.95 - -0.101 .034 .173 ,302 ,437 ,563 .693 .789 .872 .950 1.009 1.054 1.088 1.122 1.136 1.156 1.151 1.134 1.129 - -0.183 - ,184 -.175 -.175 - .163 - .16

38、9 - .167 - .171 - .166 - .162 - .I73 - .170 -. 155 -.151 - .I39 - ,136 - .120 - ,104 - ,079 . - -0.205 - .221 - .215 -.a8 - ,205 - .201 - ,211 - .220 - .221 - .221 - .214 - .214 - .213 - .202 - .194 - .178 - .146 - ,119 . . -0.957 - ,976 - .972 -.958 - .916 - .872 -.eo5 - .728 -20 -15 -10 -5 0 5 10

39、15 20 25 30 35 40 45 50 i : -0.305 -.033 .694 1.102 1.494 1.94 2.182 2.042 2.028 .354 -.059 .054 .146 .240 .334 - . -20 -15 -10 -5 0 5 LO 15 20 25 -0.158 - .256 -.a59 - .223 .117 .289 .461 .639 - .144 -.035 CT = 0.90 - - 1 -10 1 -0.132 .041 .205 -5 ,358 0 ,526 5 ,673 .825 .943 1.026 25 1.106 30 1.18

40、0 35 1.234 40 1.257 45 1.264 50 1.248 55 1.226 60 1.203 65 1.182 -0.885 - ,920 - .912 - ,892 - .e53 -.793 -.718 - .622 -.409 - .292 -.& - .064 .046 .131 .230 .302 .392 - .514 0.165 .064 ,064 .088 .172 .29 .485 .g19 .a88 1.053 -0.361 -.055 .423 .a52 1.332 2.291 2.498 2.323 1.829 2.652 -20 -15 -10 -5

41、0 5 10 15 20 25 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-0.039 0.181 .659 .130 1.182 .lea 1.626 .291 2.139 .446 2.605 .643 3.045 .a77 3.189 1.065 2.196 1.241 2.695 1.195 -0.485 -.717 - .762 - .a10 - .e75 -.912 - .959 -.9u - .e42 - f734 TABLE

42、 3.- TABUIATED AEROLVIUMIC DATA FOR Sf = a0, E, = Oo cT,s = 1.00 CT,s = 0.80 0.139 -0.715 .621 - .628 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 90 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 60 65 -0.404 - .449 -.446 -.453 - .474 -.502 - .510 -, 527 -.m - .451 - .417 -.380

43、 -.339 - .314 - .278 -20 -15 -lo -5 0 5 10 15 20 25 30 35 40 45 50 -20 -15 -10 -5 0 5 10 15 20 25 30 35 1.035 1.2w - .537 - .43l -.& - .166 -.0b7 .070 .158 .246 .330 .414 .487 CT,s = 0.60 0.145 .502 .790 1.058 1.379 1.671 1.926 2.095 1.9ll 1.783 1.708 1.602 -0.484 - ,492 - ,454 - .387 -. 273 -.128 .

44、041 .202 .303 .415 .515 .589 -0.467 -.547 -.544 - .554 -.644 CT, = 0.95 0.156 .283 .425 .554 .680 .798 .905 .997 1.066 1.113 1.167 1.176 1.1% 1.174 1.157 1.144 1.125 1.141 -0.902 -.9ll - ,881 - .a43 - .781 - .618 - .522 - .421 - .320 -.226 - .I35 -.046 .046 .124 .a35 .284 .367 - .TO4 -0.348 - .324 -

45、.330 -.330 - .328 -.39 - .345 - .349 -.347 -.340 - .328 - .318 - .294 - .276 -.246 -.228 -.201 - .169 -.6p -.Go -.662 -.603 -.529 -.488 - .427 CT,s = 0.30 -20 -15 -10 -5 0 5 10 15 20 25 0.054 .599 .980 1.348 1.780 2.168 2.557 2.761 2.334 2.104 -0.124 -.175 -.123 - .Oh1 .098 .271 .479 .680 .7& .868 -

46、0.448 -.639 - .665 - .694 -.735 -.795 - .a21 - .824 -.e26 -.664 -20 -15 -10 -5 0 5 10 15 20 25 30 35 40 45 50 55 0.170 ,275 .516 .659 .823 .974 1.102 1.191 1.266 1.319 1.352 1.346 1.344 1.320 1.283 1.235 -0.850 -.861 - .815 -.775 -. 703 -.a5 -.4* -.394 - .265 -.lP -.036 .048 .144 .=5 . 303 * 365 -0.

47、376 -.390 -.391 -.w -.398 - .417 - .416 - .425 - .421 - .419 - .397 - .364 - .333 -.305 - .272 -.244 -20 -15 -10 -5 0 5 10 15 20 25 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-20 -15 -lo -5 0 5 0.339 .836 1.215 1.572 2.028 2.455 TABLg 4.- T”ZD

48、AERODYNAMIC MA FOR 6p = W0, = 0 -0.691 -.672 - .617 -.5w - .43l - .305 -.146 - .029 .085 .1e6 .261 .3m .3m .462 -20 -15 -10 -5 0 5 10 15 20 25 YJ 35 40 45 0.315 .579 1779 .976 1.190 1.H 1.556 1.628 -0.4% - .534 -.533 - .547 -.586 -.a7 - .623 - .611 -,552 - .522 -.UT -.406 -. 365 -.330 -20 -15 -10 -5

49、 0 5 10 15 20 1.582 1.586 1.544 1.471 1.405 1.355 25 30 35 40 45 60 55 Wl c, = 0.60 80 -20 -15 -10 -5 0 5 lo 15 20 25 YJ -0.440 - .423 -.365 -.29 -.146 .017 .224 .99 .4% .%7 .514 -0.594 - .630 - .618 -.646 -.711 -.760 - .795 -.791 -.t04 -.594 - .520 0.378 .697 .956 1.215 1.595 1.863 2.122 2.267 2.W5 1