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Pressure Distributions On A 0 02 Scale Space Shuttle Orbiter Nose At Mach 21 5 In Helium
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722698805 Total Pages :78 pages Book Rating :4.6/5 (988 download)
Book Synopsis Pressure Distributions on a 0. 02-Scale Space Shuttle Orbiter Nose at Mach 21. 5 in Helium by : National Aeronautics and Space Administration (NASA)
Download or read book Pressure Distributions on a 0. 02-Scale Space Shuttle Orbiter Nose at Mach 21. 5 in Helium written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on a 0.02-scale model of the Space Shuttle orbiter forward fuselage were obtained in the 22-inch aerodynamic leg of the Langley Hypersonic Helium Tunnel Facility at a nominal free-stream Mach number of 21.5 and a ratio of specific heats of 1.67 for inclusion in the database of the Shuttle entry air data system (SEADS). The data were measured at model angles of attack of 0 deg to 50 deg in 5 deg increments for zero sideslip angle and at model sideslip angles of -5 deg to 5 deg for angles of attack equal to 5, 20, 35, and 40 deg. These data displayed trends similar to those observed in other wind tunnels at Mach 6 and 10 in air. Specifically noted is a shift in the location of the stagnation point at angles of attack above 15 deg; this effect did not, however, occur in flight. By comparison, the data obtained at Mach 6 in the Langley Hypersonic CF4 Tunnel, corresponding to a lower ratio of specific heats in the postshock region than those in helium and air, showed some reduction of the stagnation point shift at the higher angles of attack. The differences between flight and wind tunnel pressure distributions are believed due primarily to high-temperature gas chemistry effects in flight, which include lower effective specific heat ratios but which were not completely duplicated in the wind tunnels. Ashby, George C., Jr. and Bernot, Peter T. and Woods, William C. Langley Research Center...
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Book Synopsis Comparison of Predicted and Experimental Real-gas Pressure Distributions on Space Shuttle Orbiter Nose for Shuttle Entry Air Data System by : Judy L. Shinn
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