NASA NACA-TN-4041-1957 The subsonic static aerodynamic characteristics of an airplane model having a triangular wing of aspect ratio 3 I effects of horizontal-tail location and si.pdf

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1、C3CA)+-JFOR AERONAUTICSTECHNICAL NOTE 4041THE SUESONIC STATIC AERODYNAMIC CHARACTERBTICS OF ANAIRPLANE MODEL HAVING A TRIANGULAR WING OF ASPECTRATIO 3. I - EFFECTS OF HORIZONTAL-TAILLOCATION AND SIZE ON THE LONGITUDINALCHARACTERISTICSBy Bruce E. Tinling and Armando E. LopezAmes Aeronautical Laborato

2、ryMoffett Field, Calif.WashingtonJdy 1957Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARYKAFB,NMv1.NATIONKL ADVISORY COMMITTEE FOR AERONAUTIC I:lllllllllllulllllillillllll :Ooib+qTEcJItiICMINW 4041THE SUBSONIC STMIC AERYNAMIC! CHARACTERIST

3、ICS OF ANAIFi!?L!lNEMODEL HAVING A TRIANGUUiR WING OF ASPECTRATIO 3. I - EFFECTS W HORIZONP($L-TKILLOCATION AND SIZE ON TEE LONGITUDINALCHARACTERISTICS1By Bruce E. Tinling and Armando E. LopezSUMMARYAn investigation has been conductedhorizontal-tail location and size on theto determine the effects o

4、flongitudinal aerodynamic charac-teristics of an airplane model having a triangular wing. The wing hadan aspect ratio of 3 and the NACA 0003.5-63 section in the stresmwisedirection. Two horizontal tails were tested which had areas of either16.7 or 21.9 percent of the wing area. Each of the horizonta

5、l tails hadsm aspect ratio of 4, a taper ratio of 0.33, the NACA 0004-64 section,and no sweepback of the 50-percent-chordline. Tests were conducted withthe horizontal.tails located -0.10, 0, 0.10, and 0.20 wing semispansabove the chord plane of the wing at longitudinal distances of 1.2 and1.5 mean a

6、erodynamic chord lengths behind the moment center. The wind-tunnel tests were conducted at a Reynolds number of 2.5 miJJion at Machnumbers from 0.25 to 0.95.It was found that the horizontal tail was destabilizing at meratelift coefficientswhen located above the plane of the wing. When placedeither i

7、n or below the plane of the wing, the horizontal tail was stabi-lizing throughout the lift range. For the balanced condition, the dragincrement due to the tail was less when ”thetail was placed 0.10 wingsemispan below the wing chord plane than when placed in the wing chordplane. In general, the drag

8、 due to balancing the mdel decreased withincreases in tail size or length and increased markedl.yas the Machnumber was increased beyond 0.90.)X!CRODUC!KCONThe subsonic aerodynamic characteristics of a model of an airplanehaving a triangular wing of aspect ratio 3 and an all-movable horizontaltail ha

9、ve been the subect of an investigation in the Ames I! (SupersedesProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-12 NACA TN 4041k. Koenig, David G.: Tests in the Ames - by 80-FootWind Tunnel ofen Airplane ConfigurationWith an Aspect Ratio 3 Triangula

10、r Wingand an Allovable Iizontal Tail - Longitudinal smd LateralCharacteristics. NACARMAZ15, 1953. Axelson, JobnA.: Downwash Behind a Triangulsx Wing of AsyectRatio 3 - Transonic Bump Method. NACARM A53123, 1953.6. Deyomg, Johu, and Harper, Charles W.: Theoretical Symmetric SpsmLoading at Subsonic Sp

11、eeds for Wings Having Arbitrary Plan Form.NACA Rep. 921, lm.7. Sivells, James C., and Salmi, Rachel M.: Jet-Boundmy Correctionsfor Complete and Semispan Swept Wings in Closed Circular WindTunnels. NACA TN 2454, 1951.8. Herriot, John G.: Blockage Corrections fo?Three-Dimensional-FlowClosed-ThroatWind

12、 Tunnels, With Consideration of the Effect ofCompressibility. NACA Rep. 995, 1950. (SupersedesNAcARMA7B28. ).9. Heitmeyer, John C.: Effect of Vertical Position of the Wing on theAerodynamic Characteristics of Three Wing-Body Combinations. NACARMA52L15a, 1953.*.Provided by IHSNot for ResaleNo reprodu

13、ction or networking permitted without license from IHS-,-,-NACA TN 4041 13TABLE I.- G30METRIC PROPERTIES OF TEE MODELwingAspect ratio . . . . . . . . . . . . . . . . . . . . . .3.00Taper ratio . . . . . . . . . . . . . . . . . . . . . . . . 0Section . . . . . . . . . . . . . . . . . . . . . NACA ;Ax

14、es. . . . . . . . . . . . . . . . . . . . . . . . . . .Mesmaerodynsmic chord . . . . . . . . . . . . . . . . . 1.40 ftspan. . . . . . . . . . . . a71 . . . . . . a71 . . . a71 . . 3.463 ftSweepback (leading edge) . . . . . . . . . . . . . . 53.130Horizontal tailsAspect ratio. . . . . . . . . . . . .

15、 . . . . . . . . . . . 4.00Taper ratio . . . . . . . . . . . . . . . . . . . . . . . . 0.33Section . . . . . . . . . . . . . . . . . . . . . . NACA 0CK)4-64Pivot Mne (fraction of root chord) . . . . . . . . . . . . 0.45AreaLarge tail. . . . . . . . . . . . . . . . . . . . . 0.876 f%SmalJ.tail. . . .

16、 . . . . . .; . . . . . . . . ;.span0.666 ft2Large tail . . . . . . . . . . . . . . . . . . . 1.868 ftsmall tail. . . . . . . . . . . a71 *. . . . . . 1.628 ftSweepback (O.chordline) . . . . . . . . . . . . . . . . 0Vertical tail (leading and trailing edges extended to fuselagecenter line)Aspect rat

17、io (geometric) . . . . . . . . . . . . . . . . . . 1.5Taper ratio . . . . . . . . . . . . . . . . . . . . . . . . 0.16Section . . . . . . . . . . . . . . . . . . . . . NACA 0003.-64Area (to fuselage center line) . . . . . . . . . . . . 1.067 ft2span 1.290 ftSweepba;k”(;e78I6.93T 1Pivotiine J. . 72.0

18、0Dimensions in inchesFigureunless otherwise specified1 .- Geometry of the model.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18A -18664Figure 2.- Mcdel mounted in the wind tunnel.NACA TN 4041.-a71Provided by IHSNot for ResaleNo reproduction or net

19、working permitted without license from IHS-,-,-NACA TN 4041 19a Angleofattack,a,deg%“mg.=3I.0.8# 4-+-+M. o. Moment center at 0.3305, it/E = 1.19.5,t/% = 0“167 v “ 0“Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1.2I .0.8.60+. .4:zGj .2+4-0?2-.4 -40

20、 4 8 12 16 20 24Angle of Mock, a, deg .12 ,08 .04 0 -.04 -.08 -.12 m16 =20 gPitching-moment coefficient, Cm s(b) M = 0.60 LaFl?ure 7.- Continued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.,a71 I , #Angle of attack, a, deg .12 .06 .04 0 -04 +6

21、=12 +6 =20 -24PNchlng-moment coefficient, Cm(C) M = 0.80Figure 7,- Conttiued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-mcoLa 111111“0- =EZ12ZSV Z#f /I I I I I I 1 1 IKI Ir1 1 1 1 I I I 1 II I J/r 4j .21 I I I I /? I I I I I 1 1 1 1 d , vl ., ,/

22、1 A J(Mr . . A i+=-zWmI I I I I I X4 v I/1 . .,.“ fI& v 24 31 1. . 8 12 16Angle if attati, a, dig “- .16 - J2 . .04 0 .04 =08 J2 +6 -.20Pitching-moment coefficient, Cm(d) M = 0.9Figure 7.- COnttiUed-. , ,.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.-1 * Y*6E-sg*000g-1Pitching-moment coefficient, Cm(e) M = 0.93Figure 7.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-