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Assessment Of A Flow Through Balance For Hypersonic Wind Tunnel Models With Scramjet Exhaust Flow Simulation
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Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781729311233 Total Pages :56 pages Book Rating :4.3/5 (112 download)
Book Synopsis Assessment of a Flow-Through Balance for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation by : National Aeronautics and Space Adm Nasa
Download or read book Assessment of a Flow-Through Balance for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-27 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this investigation were twofold: first, to determine whether accurate force and moment data could be obtained during hypersonic wind tunnel tests of a model with a scramjet exhaust flow simulation that uses a representative nonwatercooled, flow-through balance; second, to analyze temperature time histories on various parts of the balance to address thermal effects on force and moment data. The tests were conducted in the NASA Langley Research Center 20-Inch Mach 6 Wind Tunnel at free-stream Reynolds numbers ranging from 0.5 to 7.4 x 10(exp 6)/ft and nominal angles of attack of -3.5 deg, 0 deg, and 5 deg. The simulant exhaust gases were cold air, hot air, and a mixture of 50 percent Argon and 50 percent Freon by volume, which reached stagnation temperatures within the balance of 111, 214, and 283 F, respectively. All force and moment values were unaffected by the balance thermal response from exhaust gas simulation and external aerodynamic heating except for axial-force measurements, which were significantly affected by balance heating. This investigation showed that for this model at the conditions tested, a nonwatercooled, flow-through balance is not suitable for axial-force measurements during scramjet exhaust flow simulation tests at hypersonic speeds. In general, heated exhaust gas may produce unacceptable force and moment uncertainties when used with thermally sensitive balances. Huebner, Lawrence D. and Kniskern, Marc W. and Monta, William J. Langley Research Center
Book Synopsis Assessment of a Flow-through Balance for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation by : Lawrence D. Huebner
Download or read book Assessment of a Flow-through Balance for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation written by Lawrence D. Huebner and published by . This book was released on 1993 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of a Six-component, Flow-through, Strain-gage, Force Balance Used for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation by : Marc W. Kniskern
Download or read book Analysis of a Six-component, Flow-through, Strain-gage, Force Balance Used for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation written by Marc W. Kniskern and published by . This book was released on 1990 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Method for Obtaining Aerodynamic Data on Hypersonic Configurations with Scramjet Exhaust Flow Simulation by : William R. Hartill
Download or read book Method for Obtaining Aerodynamic Data on Hypersonic Configurations with Scramjet Exhaust Flow Simulation written by William R. Hartill and published by . This book was released on 1977 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis Simulation of Hypersonic Scramjet Exhaust by : R. A. Oman
Download or read book Simulation of Hypersonic Scramjet Exhaust written by R. A. Oman and published by . This book was released on 1975 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A plan and some preliminary analysis for the accurate simulation of pressure distributions on the afterbody/nozzle portions of a hypersonic scramjet vehicle are described. The objectives fulfilled were to establish the standards of similitude for a hydrogen/air scramjet exhaust interacting with a vehicle afterbody, determine an experimental technique for validation of the procedures that will be used in conventional wind tunnel facilities, suggest a program of experiments for proof of the concept, and explore any unresolved problems in the proposed simulation procedures. It is shown that true enthalpy, Reynolds number, and nearly exact chemistry can be provided in the exhaust flow for the flight regime from Mach 4 to 10 by a detonation tube simulation. A detailed discussion of the required similarity parameters leads to the conclusion that substitute gases can be used as the simulated exhaust gas in a wind tunnel to achieve the correct interaction forces and moments.
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