NASA NACA-TN-3843-1956 Experimental steady-state yawing derivatives of a 60 degrees delta-wing model as affected by changes in vertical position of the wing and in ratio of fuselag.pdf

1、wNATIONAL ADVISORY COMMITTEEFOR AERONAUTICSTECHNICAL NOTE 3843EXPERIMENTAL STEADY-STATE YAWINGDERIVATIVES OF A 60 DELTA-WING MODEL AS AFFECTED BYCHANGES IN VERTICAL POSIIION OF THE WING AND IN RATIOOF FUSELAGE DIAMETER TO WING SPANBy Byron M. Jaquet and Herman S. FletcherLangley Aeronautical Laborat

2、oryLangley Field, Va.WashingtonOctober 1956Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECHLIBRARY this is especially true in the moderate and highranges of angle of attack or when a design departs from a simple body of.revolution (ref. 4). Exper

3、ience has shown, however, that in order toobtain more accurate estimates of the dynamic Stabilim of a given design,it is necessary.experimentally.to use stability derivatives which are determinedProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 NACA

4、TN 3843The present experimental investigationwas undertaken, as a con.tinuation of the work of reference 5, to show some effects of airplanedesign variables on the lateral derivatives of airplane models; namely,the effects on the steady-stateyawing derivatives of changes in verti-cal position of the

5、 wing for a 60 delta-wing model having ratios offuselage diameter to wing span of 0.123, 0.165, and 0.246. The deriv-atives were obtained at a Wch nuniberof 0.13 and a Reynolds ntiberof 1.65 x 106.SYMBOLSThe data presented herein are referred to theaxes shown in figure 1. The center of gravity wasje

6、ctionthroughsymbols%clCnbscEPof the wing 0.25 mean aerodynamic chord onstability system oflocated at the pro-athe fuselage center line of each model. Theused herein are defined as follows:lift coefficient, *side-force coefficient, Side forceCrolling-moment coefficient,yawing-moment coefficient,wing

7、span, ftwing area, sq ftlocal chord parael tomean aerodynamic chord,Rolling momentqSbplane passing-coefficients and.Yawing momentqSbplane of symmetry,dynamic pressure, $9 lb/sq ftmass density of air, slugs/cu ftft.Provided by IHSNot for ResaleNo reproduction or networking permitted without license f

8、rom IHS-,-,-NACATN 3843vYaPtJrOota71a71a15a71a15a15a71a15a15a71a15a15a15a15a154:0.123.a71a15.a71a15a15a71a71.of symmetry.*.*. . . . . .a71 a15a11a15a11a15a71 a15a11a11a15a11a15 .0.a71a71a15a71a15a15a15a71a156.:0.165.a71a15a15a15a15a15a15a15a71.a71a71a71a71a15a15a15a71a71a71a15a71a71a15Tail length fr

9、om center of gravity to 0.25 mean aerodynamica71a71a15a15a15a15a15a71a15a71a71a1569.00.2462.31:0376.;65AOU3chordoftail, in . . . . . . . . . . . . . . . . . . . 21.5Ratio oftailareatowing area . . . . . . . . . . . . . . 0.115Ratio oftail length towing span . . . . . . . . . . . . . 0.59.Provided by

10、 IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-qFigure L- Stabillty system of axes. Arrows indicate positive augles,velocities, and Coefficients.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN 3843 11/“

11、p/12.(W,.w4WingpOSltlM,r4.5Dmawmum dmmeter/. 5.12High ,. .- 7- -71:? - 2.2Low k - . 7+f?v/4600 maximum dfometff 7Htgh 550 . . - - -. -. -dk - - “ - - “-98tLow - . -k W900maxmwm dkmeiW/- .- - _ _Mgh - =_- _ L- 6.23.- - - - -0246Jai/ on TaI/ offcnror - cu:08 :06 -.04 :02 0 .02 .04 .06 .08Low Mid HighWmg heightW!ng sponFigure 6.- S of effects of wing position and fuselage size on thesteady-stateyawing derivatives of a 600 delta-wingmodel. u = OO.NACA -LangleyFleld, Va.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-