Transonic wind tunnel tests were conducted on an Army Missile Command (AMC) base drag research missile model in the Calspan Corporation 8-Foot Transonic Wind Tunnel during January of 1973. These tests were conducted in order to determine the effect of jet plumes on the stability characteristics of fin and ringtail afterbody configurations. Afterbody forces and moments and base pressure were measured at jet thrust levels from zero to 400 pounds. The tests were conducted at Mach numbers from zero to 1.25 and at angles of attack from -5 to +10 degrees. The report presents details of the test program, an outline of the test procedures, and results of the investigation in tabular form.
Transonic Wind Tunnel Investigation of Thrust Effects on Missile Aerodynamics
1973
278 pages
Report
No indication
English
Thrust Effects on Missile Aerodynamics
NTIS | 1971
|Investigation of Missile System Aerodynamics
NTIS | 1970