Experimental Investigation of Supersonic Flow over Axisymmetric Afterbodies with a Centered Propulsive Jet at Angles of Attack

摘要

A wind tunnel investigation of the influence of angle of attack on the flow over 5 after-bodies equipped with an axisymmetric centered propulsive jet with a Mach number of 2.5 was made. The test was performed at Mach numbers 2.0 and 3.0 at angles of attack of 0, 3, 6, 10, and 15 deg. The jet pressure was high enough to force the flow to separate from the afterbody surface. Pressure measurement, Schlieren photography, and oil flow tests were used. The boundary layer was measured at 0, 3, and 6 deg angles of attack. The flow separation can be studied from the pressure distribution and oil flow and Schlieren photographs.