Wind Tunnel Force And Pressure Tests Of Rocket Engine Nozzle Extensions On The 0 0667 Scale X 15 2 Model At Supersonic And Hypersonic Speeds

Wind-tunnel Force and Pressure Tests of Rocket-engine Nozzle Extensions on the 0.0667-scale X-15-2 Model at Supersonic and Hypersonic Speeds

Experimental Characterization of Spin Motor Nozzle Flow

"The Mach number in the inviscid core of the flow exiting scarfed supersonic nozzles was measured using pitot probes. Nozzle characterization experiments were conducted in a modified section of an obsolete M = 7.3 test section/nozzle assembly on Sandia's Hypersonic Wind Tunnel. By capitalizing on existing hardware, the cost and time required for tunnel modifications were significantly reduced. Repeatability of pitot pressure measurements was excellent, and instrumentation errors were reduced by optimizing the pressure range of the transducers used for each test run. Bias errors in probe position prevented us from performing a successful in situ calibration of probe angle effects using pitot probes placed at an angle to the nozzle centerline."--Page 3.

Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects