NASA-TM-X-213-1960 Investigation of the aerodynamic characteristics of a supersonic horizontal- attitude VTOL airplane model at Mach numbers of 1 57 2 14 2 54 and 2 87《当马赫数为1 57 2 .pdf

1、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-J ,;” ac Declassified by authority of NASA nge Not-ices #o.-LL3, . .J TECHNICAL wommm x-213 INVESTIGATION OF THE AERODyNAE4IC CHARACTERISTICS OF A SUPERSONIC HORIZONTAL-ATTImE VTOL AIRPLANE MODEL AT MAC

2、H NUMBERS OF 1.37, 2.14, 2.54, PlND 2.8p By Arthur E. Franklin and Robert M. Lust SUMMARY An investigation was made in the hngley Unitary Plan wind tunnel to determine the drag and the static longitudinal and lateral stability characteristics, horizontal-tail hinge-moment characteristics, and wing-

3、tip-nacelle pressure-distribution characteristics of a model of a super-. sonic horizontal-attitude VTOL airplane at Mach numbers of 1;57, 2.14, 2.34, and 2.87 and a Reynolds number of about 3.32 x 10 6 per foot. results of the investigation are presented without analysis. The INTRODUCTION An invest

4、igation of the aerodynamic characteristics of a model of a supersonic horizontal-attitude VTOL airplane was conducted in the Langley Unitary Plan wind tunnel. The tests were conducted at Mach numbers of 1.37, 2.14, 2.34, and 2.87. Various horizontal-tail and fuselage inlet configurations were invest

5、igated. In addition, the horizontal-tail hinge- character is t i c s and wing-tip-nacelle pressure-distribution teristics of the mode ere also deter- mined. The results o investigation are presented herein without analysis and are supplemented with summaries of the aero parameters. OL The longitudin

6、al stabil acteristics dei are referred to the stability system of axes. The lateral stability characteristics . .-t. * Title, Unclassified. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 of the model are referred to the body system of axes. are sh

7、own in figure 1. goint located at the 0.330-chord point of the wing mean aerodynamic chord and 0.29 inch above the fuselage reference line. tail hinge moments are presented about a point located at the 0.385-chord point of the horizontal-tail mean aerodynamic chord. in this paper are defined as foll

8、ows: The systems of axes used and the positive directions of forces, moments, and angles 4 The moment6 of the model are presented about a The horizontal- The symbols used span of wing or of exposed-panel surface, in. chord, in. wing mean aerodynamic chord, in. horizontal-tail mean aerodynamic chord

9、of exposed panel, in. vertical-tail mean aerodynamic chord of exposed panel, in. drag coefficient, Drag - S internal drag coefficient base drag Coefficient, Base drag S pressure coefficient Lift lift coefficient, - S Pitching moment pitching-moment coefficient, qsc rolling-moment coefficient, Rollin

10、g moment ClSb yawing-moment coefficient, Yawing moment qSb Side force side-force coefficient, qs lift-curve slope (a o0), L 3 5 5 w Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3 L 3 5 5 cqL cnP C IBV %V C 1, cD,min acm - pitching-moment-curve slo

11、pe (Cz at a = Oo)., . acL . acz ap effective-dihedral paragleter (p = Do), - per degree directional stability parameter (p = 0) , - per degree acIl ap - i cd cd 4-1 0 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 I a I I Model center line -30 d

12、i hedral line , c Oo dihedral Figure 4.-Drawings of the horizontal stabilizer of a supersonic horizontal-attitude VTOL airplane model. unless otherwise noted. Dimensions are in inches c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-S“ I In A k _. I

13、 tu S d .- tu 0 c tu L tu Y- tu I 23 a, E: a3 Yi d 2 03 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 0 Cr) a a r: rl a, 0 r: a, t a Y- a, L a, u) nr rl a, v) 3 LL. .- I rl I 8 a3 rl pt k rl a3 J Provided by IHSNot for ResaleNo reproduction or ne

14、tworking permitted without license from IHS-,-,-25 i( I v) - v) a, 0 y. I 0 a, I 3 v) v) a, I P a, 0 td Y- I ZJ fn a, rl rl Q) 0 td z .- .- - a, 0 Y- .- .- I 0 0000004) (Dod-coo+cD +curlm+cDo rlcUC9rocD4) . v) u) a, I n a, 0 cd Y- I 3 v) I t I f i- I c 0 c, td c, v) al r( rl al czl 0 td z .- a, I a,

15、 rl rl a, 0 td z m a, 2 i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 a PI nl c L a, +J X W i z I 9) c I .I rl Ct-4 0 I a Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure 9.- Variation of

16、 internal drag coefficient of a superson2c horizontal-attitude VTOL airplane model at a nominal Reynolds number 6 of 3.52 x 10 per foot. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-28 3 ri Pi k 4 cd I 0 3-4 Provided by IHSNot for ResaleNo reprodu

17、ction or networking permitted without license from IHS-,-,-in in lo A 0 cu rl 11 cn 0 0 11 U . 0 0 11 m 0 0 11 U .e n Ld v 0 0 11 cn 0 eo 11 t5 . E: a! d pc k 0 2 h 0 -P 0 ,G PI I rl d d k F.-l F: cd rl p1 Q) 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-