The effect of nose shape asymmetries on the aerodynamics of a 10 degree cone (d=5 in) was studied in ARL's 20-in.-hypersonic wind tunnel. Surface pressures were measured at various angles of attack and sideslip. Schlieren pictures were taken with a special nose model at several roll attitudes. Stability derivatives were measured by the free oscillation technique. (Author)
Aerodynamics of a Slender Cone with Asymmetric Nose Bluntness at Mach 14
1972
5 pages
Report
Keine Angabe
Englisch