An Experimental Investigation of Downstream Flow-Field Properties Behind a Sonic Jet Injected Into Transonic Free Stream from a Body of Revolution (Series II)
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL AEROBALLISTICS DIRECTORATE
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A transonic wind-tunnel investigation was conducted to determine the nature of the flow field downstream of a lateral sonic jet on a body of revolution. The survey was made in a plane normal to the body center line 8.63 body diameters aft of the lateral jet nozzle. Velocity measurements were made by a remotely driven pitot-static probe at wind-tunnel Mach numbers of 0.9 and 1.2. The data are presented in the form of Mach number vectors mapped in the normal plane for three pressure ratios and for model angles of attack of 0, 1, and 3 degrees. Results indicate a pair of trailing vortices in the jet wake on opposite sides of the jet center line. The strength and position appear to be strong functions of pressure ratios and free stream Mach number. These data indicate a method for developing means of determining aerodynamic forces on stabilizing surfaces for missiles with forward jets.
- Guided Missiles
- Fluid Mechanics