1、i RESEARCH MEMORANDUM EXPLORATORY QWESTIGATION AT MACE NUMBER 4.06 OF AN AIRPLANE CON% 22 EFFECTS OF VAXOUS TAIL ARNGEMENTS ON WING-ON z C# L. ! I q.l C. %ID WING-OFF STATIC LONGITUDINAL AND bl LATERAL STABILITY CHARACTEFUSTTCS Robert W. Dunning and Edward F. Ulmann Langley Aeronautical Laboratory r
2、ibflaav copv Langley Field, Va. I. ,* ldkf : 1535 NATIONAL ADVISORY COMMITTEE. FOR AERONAUTICS WASHINGTON April 28, 1955 -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-U - J EFFECTS OF VARIOUS TAIL ARUNGEKENTS ON WING-ON By Robert W. DurYling ard
3、 Edward F. Ulmann An investigation to determine the loagitudinal and lateral stbility characteristics of an airplane conffgurztion ha* a trzpezoidal wing with e modified hexagonel eirfoil section and a crucfformtail with 5O semimgle vedge section has been carried out in the Langley 9- by 9- inch Mac
4、h nWer 4 blmdown jet. Tests were made with and without the wing for various combinetiom of tie horizontal and vertical And ver%ical %ails in conjunc- tion vith the body and bcdy-wbg combinetion. Deteils concerning the geo- metric chmecteristlcs of the conplete eirplane rsd kir?g and tail sections ar
5、e given in tzble I and figures 3 and 4. The nodel designahions used throug3out the report axe graphically illustrated a figure 5. The wing has e tragezoidal plan forn with a hexagonal section tht has been modi- fied by rounding the leadling edge to t 1-percent-chord radius and blunting the treiling
6、edge to a 2-percent-chord thickness. The wing hzs a maxirnum thickness of 4 percent, and the quarter-chord. Une is swest 290. The tails have a trapezoidal plan form, a 5 semiangle wedge section, and a cor?figuration installed in the T-langley 9- by 9-inch Mech number 4 blov- down jet is presented in
7、 figure 6. I O.OO7-inch 1eaCi.ng-edge radius. A photogrash of the comglete airplane I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 TESTS The settling-chamber stagnakion terqerature during any single run varied from approx-imately 80 F to 40 F, a
8、nd the settling-chamber stag- nation pressure was held at approxinately 186 parnds per sqwe inch absolute. These conditions correspond approxinately to a Reynolds number of 2.7 x 106 based on the wing mean aero6ynamic chord. The tests were run at humidities below 5 x pounds of water vapor per pmd of
9、 dry air, which is believed to be low enough to eliminate water-condensation effects. The test-section static temperature and pressure did not reach the point where liquefaction of air would take place. Data were obtained for angles of attack from Oo up to Eo at angles of sideslip fron Oo up to 8O.
10、CISIN OF DATA Tne probable uncertainties in the test data due to the accuracy limi- tations of the balance and recording equipment and the ability of the system to reseat data points are listed in the following table: (The accuracy of the rolling-moment coefficients is low relative to the Itiaxirmun
11、 rolling moment encountered. Tds low accuracy occurred because rolling- moment gages were added to an existing balance which was not originally designed to measure rolling monent.) CN t0.001 Cy . f0.0003 ko.0004 cn f0.0000 c2 . *o.ooog a,aeg f0.1 P,Cieg M.1 The experiaental static serodynamic charac
12、teristics of the configu,ra- tions are given in table I1 for all the angles of attack and sideslip tested, and representative garrts of the data are presented in the figures. Equations for tracsferring these coefficients from the body axes to the stability axes are Provided by IHSNot for ResaleNo re
13、production or networking permitted without license from IHS-,-,-NACA RM 5508 .I 1 . t 5 cys = cya c I C cos u + C sin a 2s zB ns % = cos CL - c sin a 2B cps; = c% Inasmch as 1ongi.i;Uaim.l Torces were not measured, the axes triissfer equ-bions for lilt and dra.g coefficients are not gL 1 yen. The st
14、etic longitudlnel characteristics of the node1 are presented in figures 7 and 8. Figure 9 presents the longitudinal stabilLty deriv- ative acdac, for several tail configurations. The effects of sideslip angle on the laterel and longitudinal charac- teristics of tine mOaels axe presented in figures 1
15、0 to 13. Figure 14 pre- sents the static lateral stzbility pmameters kB, elg, and cy0 for several tail configuratlians. Variations of the lateral. chmscteristics with mgle of attack are presented in figures 15 to 17, and figure 18 pre- sents %he variatim- of the sdtic lateral chazacterfstics with no
16、rmal- force coefTicient for several tail configurations. Lanaey A-eromutical Laboratory, National Advisory Committee for Aeromukics, Lzngley Field, Va., March 21, 1955. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 REmNCES 1. McLellan, Charles H.
17、: A Elethod for Increasing the Effectiveness of Stabilizing Surfaces at High Supersonic Mach Numbers. NACA RM L5hF21, 1954. 2. Dunning, Robert W., and ulmam, Edwd F.: Static Longitudinal and Lateral Stebility Data From an Exploratory Investigation at Mach Number 4.06 of an Airplane ConfYguration Hav
18、ing a Wing of Trape- zoidal Plan Form. NACA RM L55A21, 1955. 3. Penlana, 3Fm A., Ridyard, Herbert W., and Fettem, David E., Jr.: Lift, Drag, and Static Longitudinal Stability Data ion at a Mach Number of 6.86 of en Airplane Configuration Raving a Wing of Trapezoidal Plan Form. NACA RM L55Ula, 1955.
19、5. Dunnirg;, Robert W., and Ulmann, Edward F. : Exploratory Investigation at Mach Number 4.06 of an Airplane Configuration Having a Sign of Trapezoidal Plan Form - Longitudiml and Lateral Control Character- istics. NACA RM 5528, 155. 6. Fetterman, David E., Jr., Penland, Jin A., and Ridyard, Herbert
20、 W.: Static Longitudinal and Lateral Stability and Control Data From an Exploratory Investigation at a Mach Number of 6.86 of an Airplene CorSiguration Having e Wing of Trapezoidal Plan Form. NACA RM L55C04, 1955 .# 7. Ulmenn, Fdward F., and Lord, Douglas R.: An Investigation of Flow Characteristics
21、 at Mach Number 4.04 Over 6- and 9-Percent-Thick Symmetrical Circular-Arc Airfoils Raving 30-Percent-Chord Trailing- Edge Flaps. NACA RM L51D30, 1951. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-7 z Wing: kee. (incluaing M = 4.06; R = 2.7 x 104 -
22、 Continued (b) Body with upper vertical tail - Concluded 0 1 2 i 6 8 0 1 2 3 L 6 8 10 0 1 2 3 tl 6 I20 1 2 3 Lt 6 i 1 0. oooo 0 0003 .0006 . 0011 . 0016 . 0025 . 0036 .oooo . 0002 e 0003 0007 0010 . 0021 . 0026 . 0000 -0 0002 -0 mc4 -0 0003 -0 oO01 . 0010 e 0001 -0 0010 -* m11 00 0009 *oooo “ -0 OOC
23、G Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 - NACA RM L55DO8 TAU 11.- STATIC LONGITUDINAL AND LATEHAL AERODYNAMIC CHARACTEBISTICS OF t AN AIRPLkhi CCWIGUKATIOI4 AND VARIOUS CCMBINATIOllS OF ITS CWPONEhTS LODY-AXIS AATA; M = 4.06; R = 2.7 X 1
24、.61 - Continued (c) Body with lower vertical tail L J 1 - 6 - 0 1 2 3 4 6 6 0 1 2 3 h 6 8 0 1 2 3 L 6 8 0 1 2 3 4 6 8 - - - -0.0002 . 0001 . 0005 .oO08 .ool4 00026 047 -* COO2 . 0002 eoo6 . 0010 0015 0028 0052 -0 0002 . 0003 . 0008 . 0012 .0018 003L 0057 -0 0002 a003 . 0010 0016 002L .a3 0063 Provid
25、ed by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NP-CA E4 L53Do8 -1c, ll m TABLE 11.- STATIC mBGITLIDINAL AIID LATERAL AERUDXNAKC CHkRACTEIPISTICS OF I AN AiBPLANE CONFIGWTION AND VARIOUS CCM3INATIONS OF ITS COhlPONENlS bODY-AXiS DATA; M = 4.06; R = 2.7 x 1
26、06f - Coctinued 1 (c) Body with lower vertical tail - Concluded f I t f I 0 t ,0717 1 002113 I I 1 I I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-12 s TABLE 11.- STATIC LONGITUDIML AND LATERAL AERODYNUIC CHARACTERISTICS OF AN AIRPLANE CONFIGURAT
27、ION AND VARIOUS CUNBIUTIONS OF ITS COMPONENTS I LODY-AXIS DATA; M = 4 -06; R = 2.7 X 104 - - Continued Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. TABLE IIoo STATIC LONGITUDINAL AND LABRAL AEROIIYWIC CHARACTERISTICS OF C AN AIRPLANE COISFIQUEiA
28、TION AND VARIOUS CMBINATIONS OF ITS COWOhiNTS CHJY-AXE3 DAW; M =: 4.06; R =: 2.7 x 1063 - Continued f (e) Body with horizontal tail - Concluded 0 1 2 3 Ir 4 8 6 0 1 2 I! 8 0 1 2 7 “ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 NACA RM 5308 TABL
29、E 11.0 STATIC LONGITUDINAL AND LATEHAL AERODYNAMIC CHARACTEilISTICS OF AN AIRPLANE CONFIGURATION UD VARIOUS COMBINATIONS OF ITS COMFONENTS BODY-AXIS DAICA; M = 4.06; R = 2.7 x 1061 - - Continued - (f) Bow with horizontal and upper vertical tails 0 1 2 3 h 6 8 0 1 2 3 4 6 8 - t 1 i 6 Provided by IHSN
30、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 11.- STATIC LONGITUDINAL AND LATERAL AERODYNAXIC CHARACTERISTICS OF 1 AN AiItPL4NE COWIGURATION AMJ VARIOUS COHBINATIONS OF ITS COMPONENTS bDY-AXIS D.KE!A; M = 4.06; R = 2.7 x 1061 - Continued I- Il I I Provided
31、by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 TABLE 11,- STATIC IDNGITUDINAL AND LATERAL AERODYNAMIC CHARACTERISTICS OF (i) Body-wing combination See table 11( c) , reference 2. Provided by IHSNot for ResaleNo reproduction or networking permitted without
32、license from IHS-,-,-5. AN AIRPLANE CCMFIGURATIOI AND VARIOUS COMBINATIONS OF ITS CCWONEhiTS LBODY-AXIS DATA; M = 4.06; R = 2.7 x 10q- Continued d (j) Body-wing combinstion with upser verticalteil 0 1 2 3 4 5 6 7 8 0 1 2 1 5 6 7 8 0 1 2 - i 5 6 7 8 0098 00102 ,0102 0104 0 0105 0 012s 0 Oll5 0123 012
33、4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18 MI_. NACA RM 5908 . TABLE 11.- STATIC LOGITUDINAL AND LATERAL AEROmNAYIC CHARACTERISTICS OF i AN AIRPLANE CONFIGURATION AND VARIOUS COMBINATIONS OF ITS CadPONENTS bODY-AXIS DATA; M = 4.06; R = 2.7
34、x 103 - Continued (j) 3ody-wing combination witn ugper vertical tail - Concluded - - i - i 10 i 0 1 T “ 0.1231 e 1250 .I238 . 1236 e1 221 . 1218 1250 d2t2 . 1256 T t I 0.9187 . c191 . 01% . 020s . 0202 .0206 e 0212 0213 . C218 . 0213 . a218 e 0226 e0235 . 0239 .e269 A264 .0269 00276 Provided by IHSN
35、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE r1.- STATIC LOGITUDINAL AND LATERAL AERODYNAMIC CHARACTERISTICS OF (k) 0 1 2 3 4 6 8 0 1 2 l 6 8 0 1 2 3 L 6 8 0 1 2 3 M = 4.06; R = 2.7 x 1Oq - Continued a j (k) Body-wing combination with lower vertical -tail -
36、 Concluded I Oe 1812 1791 01770 6 1788 1785 1833 1780 * 232 M = 4.06; R = 2.7 x l.Oq - Continued I cN c2 c!l c* CY (2) Body-wing collrbination with verticd tails 0 0 1 1 2 2 3 3 4 4 5 0 1 2 3 M = 4.06; R = 2.7 x 10q- Continued (1) Body-wing combination with vertfcal tails - Concluded I Provided by I
37、HSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 11.- STATIC mrmmm AND LATERAL AEROJJYNAIIIC CHARACTEFUSTICS OF I AN AIRPLAIYE CONFIGURATIOpi AND VIsRIollS COMBIIUT1:ONS OF ITS COUPONENTS 5 (m) Body-ving cocibinat5on with horizontal teil - Concluded c “ + I
38、(n) Body-wlng combination with horizontal and upper vertical tails See table II(b), reference 5. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 11,- STATIC LOGITUDINAL AND LATERAL AERODYNAMIC CHARACTERISTICS OF AN AIRPLANE CONFIGURATION AND VA
39、RIOUS COKl3INATIONS OF ITS COMPONENTS FODY-AXIS UWAj M = 4.06; R = 2.7 x l.Oj - Continued (0) Body-wing cambination with horizontal and lover vertical tails See table 11( c) , reference 5. (p) Body-wLng combhation with cruciform tail See table II(a) , reference 2. I 0 i i 2 - 0 0 1 1 2 2 3 3 5 6 - P
40、rovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure 1.- Camplete-model ccnflguration. L-86688 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure 2.- Systems or“ reference axes. Subscript B indic
41、ates body exes; subscript S indicates stability axes. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i i“ Radius = 6.85 2.368 2.530 & 2.602 7.500 ,-Moment reference - t -0.790- 12.290 -4 Figure 3.- Wind-tunnel model. All dimensions are in inches. Pr
42、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 NACA RM L55008 .01 c radius eo4 c J. I -02 c I - .OO7 in. radius I c (b) Horizontal and vertical tails. Figure 4.- Wing and tail airfoil sections used on model. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
