Experimental Investigation Of The Sudden Expansion Of Supersonic Flow Into A 90 Vee Shaped Channel PDF Download

Results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves are compared with predictions of theory. The location of the detached shock wave was determined from schlieren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. At a Mach number of 1.9, the form of the detached wave and the pressure distribution over the body were investigated for each nose shape. In addition, the relation between shock location and flow spillage was determined for several axially symmetric nose inlets.