Results of a Transonic Wind Tunnel Investigation of Trust Effects on the Aerodynamics of the Longbow Missile Configuration.

摘要

Transonic wind tunnel tests were conducted on a strut-mounted model of the LONGBOW missile configuration to determine thrust effects on a body of revolution afterbody with fins located at various longitudinal positions. Thrust was simulated by a cold air axial jet. Base pressure and afterbody forces and moments were measured. The test was conducted at Mach numbers from 0.4to 1.25and at angles of attack from -2degrees to 10degrees. Jet thrust was varied from 0to 400pounds. Reynolds number per foot varied from 0.7to 1.7million. (Modified author abstract)