NASA-TM-X-3128-1974 Experimental aerodynamic characteristics for a cylindrical body of revolution with various noses at angles of attack from 0 deg to 58 deg and Mach numbers from .pdf

1、ANDNASA TECHNICAL .25-. 50-.75-1 .0 0 . 0 10 20 30 40 50 60ALPHA2-00-2- - 5-10 1, - -15- - - - - -0 10 20 30 40 50 60ALPHA(c) CA and C., versus a.Figure 5.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SYMBO. CONFIGURATION OESCRIPTIONNI

2、ClN2 CIN3 ClN7 CIz - -10 04-2 I . . I . . . .0 10 20 30 40 50 60ALPHA2 0 m ii. ri.- - Ti-i. i ri-r -. . r r i- ri -r i- . . . . “r- - - - - - - - - - - - - - - - - - -0o5-0 10 20 30 40 50 60ALPHA(a) Xacd and CN versus a.Figure 6.- Effect of nose fineness ratio;M = 1.5, Re = 3.8X10s.Provided by IHSNo

3、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-Il)- SYMBOL CON FIGUATION DESCRIPTIONNI ClN2 CIN3 ClN7 Cl.50.25- .50U I1-1U-.75-1 .00t . . . U 10 20 30 40 50 600 10 20 30 40 50 60ALPHA-2(b) Cy/CN and Cy versus a.Figure 6.- Continued.Provided by IHSNot for ResaleNo re

4、production or networking permitted without license from IHS-,-,-SYtMBOL CFIGlRATI N DESCRIPTIIONNI ClN2 ClN3 ClN7 C!.50 I . i i .Ii . i-. i i-I.25-S0M- .25 - - -.50U-.75-1.00- 1 .25 i. 1 . . . . . . . n u. .u LLLALL . n . . .0 10 20 30 40 50 60ALPHA1 . . . . . . . . . . . . 5-5- - - - 44- -10-15 -0

5、10 20 30 40 50 60ALPHA(c) CA and Cn versus a.C, Figure 6.- Concluded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SYMBOL CONFIGRATION DESCRIPTIONNI ClN2 CIN3 ClN7 CI10 - - . . . . .I . . n. n r I, -T- J , l . T l - . . . T 1 . l -i.- - - - - - - - - - - - - -U1-4-0 10 20 30 40 50 60ALPHA(a) xacN d and CN versus a.Figure 7.- Effect of nose fineness ratio0 M = 2.0 Re = 3.8X10Figure 7.- Effect of nose fineness ratio;M = 2.0, Re =3.8X 10g.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-