1、RESEARCH MEMORANDUM LOW-SUBSONIC INVESTIGATION TO DETERMINE THE CHORDWISE PRESSURE DISTRIBUTION AND EFFECTIVENESS OF SPOILERS ON A THIN, LOW-ASPECT-RATIO , UNSWEPT , UNTAPERED, SEWISPAN WIMG PlND OM THE WIMG WITH LEADmG- AMD TRBrnG-EDGE FUR By Wwin R. Croom Lang1ey Aeronautical Laboratory LmgLey Fie
2、ld, Va. NATIONAL ADVl SORY COMMITTEE FOR AERONAUTICS I WASHINGTON April 23, 1958 t ?+ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1J TtACA RIvi 5805 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS RESEARCH WORANDUM LOW-SUBSONIC INVESTIGATION TO DETER
3、MINE THE CHORDWISE PRESSURE DISTRIBUTION AND EFFECTIVENESS OF SPOILERS ON A THIN, LOW-ASPECT-RATIO, UNSWEPT, UNTAPERE=D, SEMISPAN WING AND ON THE WING WITH LEADING- AND TRAILING-EDGE FLAPS By Delwin R. Croom SUMMARY An investigation was made in the Langley 300-MPH 7- by 10-foot tunnel to determine t
4、he effect of spoilers on the static longitudinal and lateral aerodynamic characteristics and the chordwise pressure distribution on a thin, untapered, unswept, semispan wing having an aspect ratio of 3.33 and NACA 65004 airfoil sections. The wing was equipped with leading-edge flaps and trailing-edg
5、e flaps. Results of the investigation, without discussion, are presented in the form of static longitudinal and lateral aerodynamic characteristics and tabulated pressure coefficients, section normal-force coefficients, and section pitching-moment coefficients. Considerable interest has been shown i
6、n the use of spoilers for lateral control and gust alleviation. The spoiler is more effective as a lateral control when it is located in a more rearward position, and, as pointed out in references 1 and 2, the spoiler is more effec- tive as a gust alleviator (reduces the lift-curve slope) when it is
7、 located in a more forward position. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACA RM L5805 The present investigation was made in the Langley 300-MPH 7- by 10-foot tunnel to obtain the static longitudinal and lateral aerodynamic characterist
8、ics and the chordwise pressure distribution at the 60-percent- semispan station over a thin, low-aspect-ratio, unswept, untapered, semi- span wing with a 10-percent-chord projection spoiler of various spans located at various chordwise locations on the wing with leading- and trailing-edge flaps. The
9、 results of the investigation are presented without discussion. Pressure coefficients, section normal-force coefficients, and section pitching-moment coefficients are presented in tabular form. SYMBOLS chord, ft plain-wing chord, ft trailing-edge-flap chord, ft leading-edge-flap chord, ft wing span,
10、 ft wing area, sq ft Twice semispan lift lift coefficient, qoos slope of lift curve of basic model (measured at a = 0) per degree slope of lift curve of model with spoiler (measured at a, = 0) per degree Twice semispan drag drag coefficient, qoos jet-boundary correction applied to drag coefficient p
11、itching-moment coefficient of wing referred to wing quarter- Twice semispan pitching moment chord, qwscw Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L58BOFJ 3 Rolling moment caused by spoiler rolling-moment coefficient, qwSb yawing-moment
12、 coefficient, Yawing moment caused by spoiler %Sb ptLw - P pressure coefficient, (where subscripts u and qm 2 denote upper and lower surfaces, respectively) 2f distance from wing quarter-chord to hinge line of trailing- edge flap measured parallel to trailing-edge-flap chord, ft distance from wing q
13、uarter-chord to hinge line of leading-edge flap measured parallel to leading-edge-flap chord, ft x longitudinal distance, ft X f distance from hinge line of trailing-edge flap to center of load on trailing-edge flap, ft X N distance from hinge line of leading-edge flap to center of load on leading-e
14、dge flap, ft Y lateral distance, ft free-stream total pressure, lb/sq ft t,m P local static pressure, lbtsq ft 2 4, f ree-stream dynamic pressure, - “ , lb/sq ft 2 P mass density of air, slu;s/cu ft v free-stream velocity, ft/sec 6f trailing-edge-f lap deflection (positive direction, trailing edge d
15、own), deg % leading-edge-flap deflection (positive direction, nose of flap down), deg a angle of attack of chord plane set in tunnel, deg jet-boundary correction applied to angle of attack, deg Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM
16、L58BO5 ac corrected angle of attack, deg c section normal-force coefficient of trailing-edge flap based NJ f on trailing-edge-flap chord c section normal-force coefficient of leading-edge flap based 37 N on leading-edge-flap chord N,w section normal-force coefficient of that portion of wing between
17、leading-edge and trailing-edge flaps based on plain-wing chord C N,w wing section normal-force coefficient based on plain-wing chord (chord force of leading-edge flap and trailing-edge flap neglected), Cm, f section pitching-moment coefficient of trailing-edge flap based on trailing-edge-f lap chord
18、 (moments taken about trailing- edge-flap hinge line) m, N section pitching-moment coefficient of leading-edge flap based on leading-edge-flap chord (moments taken about leading-edge- flap hinge line) Cm,w section pitching-moment coefficient of that portion of wing between leading-edge and trailing-
19、edge flaps based on plain- wing chord (moments taken about wing quarter-chord) C m,w wing section pitching-moment coefficient based on plain-wing chord (moments taken about wing quarter-chord; chord force of leading- and trailing-edge flaps neglected), MODEX AND APPARATUS The model was tested in the
20、 Langley 300-MPR 7- by 10-foot tunnel by means of the semispan technique with the ceiling of the tunnel as the reflection plane. The geometric characteristics of the semispan wing used in this investigation are given in figure 1. The wing had O0 of sweep, a taper ratio of 1, an aspect ratio of 3.33,
21、 and Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM 5805 5 NACA 65004 airfoil sect ions parallel to the f ree-stream direction. The wing was equipped with leading-edge and trailing-edge flaps. The leading- edge-flap chord was 15 percent of t
22、he wing chord, and the leading-edge flap pivoted about the lower surface along the 15-percent-chord line. (see fig. 2. ) For the deflected condition the break in the upper surface was faired to an arc of a circle. The sealed trailing-edge-flap chord was 25 percent of the wing chord. (see fig. 2. ) T
23、he leading-edge flap, the trailing-edge flap, and the wing were constructed with flush-surface pressure orifices located at the 60-percent-semispan station. The 10-percent-chord projection spoiler used in this investigation was made of wood to the dimensions shown in figure 2. The spans, span- wise
24、locations, and chordwise locations of the various spoiler arrange- ments are indicated in figure 2. TESTS The tests were made in the Langley 300-MPH 7- by 10-foot tunnel at a dynamic pressure of approximately 25 pounds per square foot. For these tests, the leading-edge flap was deflected at 0 or 30
25、and the trailing-edge flap was deflected at 0 or l5O. The spoiler had a pro- jection of 10 percent chord and was tested as a full-semispan control, a half-semispan inboard control, and a half-semispan outboard control hinged at the lo-, 30-, 50-, TO-, and 90-percent-chord locations. (see fig. 2. ) T
26、he maximum angle-of-attack range for this investigation was from about -12 to 24. Chordwise pressure distributions were obtained at the 60-percent-semispan station. CORRECTIONS The jet-boundary corrections applied to the data of this paper were obtained by the method outlined in reference 3 and are
27、as follows: The blockage correction as applied to the dynamic pressure was obtained by the method outlined in reference 4. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-RESULTS The results of this investigation are presented without discussion. The
28、 order of presentation in the figures and tables is as follows: Static longitudinal and lateral aerodynamic characteristics: Figure alf-span inboard spoiler; SN = 0; S = o0 . 3 Half-span outboard spoiler; % = 0; Sf = 0 4 Nl-span spoiler; % = 0; Sf = 0 . 5 Half-span outboard spoiler; SN = 0 and 30; 6
29、f = 0 and lJO. 6 Nl-span spoiler; SN = 0 and 30; Sf = 0 . 7 Lift-curve-slope comparison . 8 Chordwise pressure distribution: Basic model; GN = 0; tjf = o0 9 0 Half-span inboard spoiler; SN = 0; Sf = 0 10 to 14 alf-span outboard spoiler; SN = 0; 6f = o0 . 15 to 19 1-span spoiler; SN = 0; S = o0 20 to
30、 24 . Half-span outboard spoiler; SN = 30; Gf = 0 and 15 25 to 28 Full-span spoiler; % = 30; Sf = 0 . 29 to 32 Tabulated integrated section data: Table Half-span inboard spoiler; % = 0; Sf = 0 . I Half-span outboard spoiler; FN = 0; Sf = o0 II Nl-span spoiler; % = 0; Sf = 0 . I11 Half -span outboard
31、 spoiler; SN = 30; Sf = 0 and 15 IV ull-span spoiler; 6 = 30; tif = o0 v Since the location of the pressure orifices is at the 60-percent- semispan station, the section data for the full-span and half-span out- board spoilers show the effect of the spoilers on the section loading; whereas the sectio
32、n data for the half-span inboard spoiler give an indication of the carryover of the load outboard of the spoiler. It should also be pointed out that these data are for only one value of spoiler projection and, although they are useful in determining the Provided by IHSNot for ResaleNo reproduction o
33、r networking permitted without license from IHS-,-,-NACA RM L58BO5 7 effects sf the several variables, they are not necessarily applicable to the design of a control surface that uses small deflections. A method has been developed by the Data Reduction Branch of the Langley Instrument Research Divis
34、ion whereby the IEM type 407 accounting machine can be used to obtain approximate plots of data as they are tabulated. This tabulator was used to obtain the plots of figures 9 to 32, and even though they are not as accurate as may be desired, they do show trends of the pressure distribution. An accu
35、rate tabulation of these data is provided at the left of these figures. Langley Aeronautical Laboratory, National Advisory Committee for Aeronautics, Langley Field, Va., January 14, 1958. 1. Croom, Delwin R., Shufflebarger, C. C., and Iluffman, Jarrett K.: An Investigation of Forward-Located Fixed S
36、poilers and Deflectors as Gust Alleviators on an Unswept-Wing Model. NACA TN 3705, 1956. 2. Croom, Delwin R., and Ruffman, Jarrett K.: Investigation at Low Speeds of Deflectors and Spoilers as Gust Alleviators on a Model of the Bell X-5 Airplane With 35 Swept Wings and on a High-Aspect-Ratio 35 Swep
37、t-Wing-Fuselage Model. NACA TN 4057, 1957. 3. Polhamus, Edward C. : Jet-Boundary-Induced-Upwash Velocities for Swept Reflection-Plane Models Mounted Vertically in 7- by 10-Foot, Closed, Rectangular Wind Tunnels. NACA TN 1752, 1948. 4. Herriot, John G. : Blockage Corrections for Three-Dimensional Flo
38、w Closed-Throat Wind Tunnels, With Consideration of the Effect of Compressibility. NACA Rep. 995, 1950. (supersedes NACA RM A7B28. ) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L58BO5 WBLE I.- UPPtGNLTZ SElIVIl DAli pf = 00; 6 = oO; has-s
39、pan inboard spoiler I ,2258 40038- ,8353 ,5998 81257 ,0512- 8 ,3756 .0020- 1.3665 ,8107 ,1447 ,0574- a5769 ,0266- 1.4029 ,7538 ,1509 ,0547- ,7309 ,0850- 1.2423 06649 ,2729 ,0989- ,8171 ,1055- 1.3373 ,1147 ,3480 -1315- Spaller hlnged at 0.7 so893 10192 65364 ,3547 ,0840- ,3469 ,2254 a0200 ,9781 ,6458
40、 ,0596- ,2806 ,3567 -0202 1.4287 ,8493 $0376- ,2227 a5520 ,0131- 1.3880 87440 ,0054 ,1112 7508 ,0694- 1.3633 ,7253 ,0792 ,0646- Spoiler hrnged at 0.9 ,2350- 60516 ,3811- ,2351- ,2312- a1461 4 00355 ,0546 ,5271 ,3489 $1751- ,1224 ,1785 ,0569 09985 ab569 ,1494- ,1139 ,3390 ,0558 105475 ,9289 ,1090- ,0
41、994 ,5120 a0248 1.4831 17871 ,0403- ,0717 ,6764 ,0205- 1.4764 r7836 ,0604 ,0370 ,7855 ,0451- 1.5930 ,8444 ,1332 a0133 ,8423 a0777- 1.5463 ,8191 ,2423 ,0222- ,7948 .1000- 1.3294 ,7091 ,3386 a0587- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA R
42、M L58BO5 mm 11.- nmmm SECTS011 QAm 6* = 0; rjI1 = 0; half-span outboard spoiler I 0 ,0361 ,0940- 1.2086- 115929- a0826 ,0309- 4 st443 ,1149- ,5915- ,7422- ,2345 ,4067- 6 ,3569 a1310- ,3367- .3973- ,3231 ,6211- 8 ,4301 ,1298- 80005- .0000 ,3640 ,7250- 10 ,5429 a1293- ,4409 ,5191 ,3894 .7077- 12 ,7164
43、 ,1208- 1.2129 1.3324 ,3913 ,7966- 14 a7736 a1205- 1.3771 1.4547 14065 ,8270- 16 ,7560 ,1243- 1.3663 1,4560 .4603 ,9616- 4 -1019 .0875- ,0708 .I022 ,3328 61371- 6 62013 ,0821- 64066 ,3196 a3326 ,1355- 8 .3757 ,0849- ,9231 ,6538 ,3834 ,1547- 10 6044 ,0868- 1.4626 a9476 a4045 ,1616- 12 .7747 ,1018- 1.
44、2611 ,6724 ,3390 ,1301- 14 -7886 ,1022- 1.2834 ,6778 ,3456 ,1325- Spoiler hinged at 0.X 4 e0117- ,0125- 83320 62987 ,2398 r1072- 6 ,1084 ,0093- a7464 65053 ,2524 1126- 8 -2990 ,0166- 163250 ,8436 3120 ,1365- 10 .5268 ,0387- 1.6475 ,8991 ,3895 ,1654- 12 -7660 ,0903- 1.4249 17533 ,4250 1808- 14 -7806
45、,0988- 1.3589 ,7227 ,4024 ,1621- 16 ,8050 .1054- 1.3528 ,7231 ,3902 a15b3- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L5805 TABLE XI.- INTxwArn smmoii DAm 8 - oO; % = oO; full-span spoiler Cf - I Spoiler hinged at O.lc 4- 2519- -1156- 1.
46、8637- 2.3307- ,2106 ,3387- 0 ,0365- ,1286- 1.6296- 2,1067- ,2656 ,4685- 4 1342 a1257- ,9891- 1.2711- ,3056 ,5675- b ,1932 ,1240- a7737- ,9776- ,3213 a6061- 8 ,2520 ,1192- .5309- .6484- ,3262 ,6200- 10 -3117 ,1144- -2781- -3271- ,3260 a6203- 12 a4637 ,1108- ,3825 a3800 ,3612 ,7090- 14 ,5736 ,1084- ,8
47、497 ,8720 ,3826 a7662- 16 ,7145 ,1115- 1.3749 1.4542 ,4277 ,8821- 18 ,8571 ,1151- 1.8859 2.0187 ,4708 ,9941- Spoiler hinged at 0.3 4- ,4900- ,0855- 1.8967- ,9840- ,1379 a0555- 0 ,2769- ,0803- 1.1927- ,7151- ,1809 ,0757- 4 ,0428- ,0847- ,3905- al88O- ,2658 ,1136- 6 ,0468 ,0823- m0745- 0200 ,2836 ,120
48、2- 8 e1561 a0791- a2797 ,2498 a2976 ,126k- 10 ,3268 ,0805- ,7309 a4916 ,3422 ,1446- 12 ,6310 a0910- 1.1993 a6600 ,3744 ,1518- 14 ,7551 ,1039- 1.2443 ,6618 ,3725 ,1494- 16 .8251 a1110- 1.3547 -7084 ,4090 ,1608- 18 a8360 ,1185- 1.3755 a1244 ,4524 ,1803- Spoiler hinged at 0.5 4- ,6092- ,0413- 1.9362- 1.0764- ,1519 ,0622- 0 ,3887- a0160- ,8769- $5267- 1564 ,0682- 4 $1486- ,0129- -0542- -0004 ,2156 ,0926- 6 ,0272- -0131- ,3427 ,2569 ,2392 e1042- 8 a0875 .0111- -7131 ,4996 ,2545 a1106- 10 42785 -0143- 1.1367 a6667 -2439 01075
