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>Part I. The effect of a simple throat distortion on the downstream flow in a hypersonic wind tunnel nozzle. Part II. An experimental investigation of flow over simple blunt bodies at a nominal Mach number of 5.8
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Part I. The effect of a simple throat distortion on the downstream flow in a hypersonic wind tunnel nozzle. Part II. An experimental investigation of flow over simple blunt bodies at a nominal Mach number of 5.8
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.PART ONEAn experimental investigation was conducted in the GALCIT 2 1/2 inch Supersonic Wind Tunnel to determine the effect of a known distortion of the throat section of a hypersonic nozzle on the flow in the region downstream from the throat. The flow in a nozzle with a rectangular throat section was compared with the flow in the same nozzle with the throat region distorted to produce a throat height which varied linearly across the throat section. The flow was investigated by means of Pitot pressure surveys in the horizontal plane of symmetry of the undistorted nozzle.The magnitude of the effect produced by the throat distortion was observed to be approximately that predicted by one-dimensional isentropic flow relations. However, the sign of the effect was reversed in about the distance required for a curved Mach line starting at the throat to cross the channel.PART TWOAn experimental investigation was conducted in Leg No. 1 of the GALCIT Hypersonic Wind Tunnel to determine flow characteristics for a series of blunt bodies at a nominal Mach number of 5.80 and free stream Reynolds numbers per inch of [...], [...] and [...]. The scope of this investigation was to determine surface static pressure distributions and to obtain schlieren photographs showing the shock configurations. The seven bodies investigated were as follows: (1) 40[degree] half-angle cone; (2) 40[degree] half-angle cone with spherical nose; (3) hemisphere-cylinder; (4) cylinder transverse to the free stream flow; (5) flatnosed cylinder with its major axis parallel to the free stream flow direction; (6) 10[degree]-40[degree] half-angle double cone; and (7) 13[degree]-30[degree] half-angle double cone. All tests were conducted in one-phase flow with a tunnel stagnation temperature of 225[degrees]F and with models at zero angles of attack and yaw.
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