INVISCID VELOCITY PROFILE PRODUCED BY AN AXISYMMETRIC CONTOURED NOZZLE FOR AN ARCHEATED HYPERSONIC WIND TUNNEL.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The study experimentally investigated equilibrium and non-equilibrium flow at the exit of a 9 12 inch diameter axisymmetric contoured hypersonic nozzle. The flow was probed with an impact pressure probe, and steady state and transient calorimeters, and the velocity was calculated from these data. The shape of the resulting velocity profiles showed that the nozzle produced uniform parallel flow, and that the nozzle design method was adequate for use in designing a 5.5 foot diameter contoured nozzle to produce equilibrium flow up to Mach 10 and non-equilibrium flow at Mach numbers of 11-15 in an arc-heated hypersonic tunnel. Author