Results of a M = 5. 3 Heat Transfer Test of the Integrated Vehicle Using Phase-Change Paint Techniques on the 0. 0175-Scale Model 56-Ots in the NASA/Ames Research Center 3. 5-Foot Hypersonic Wind Tunnel
Results of a M = 5. 3 Heat Transfer Test of the Integrated Vehicle Using Phase-Change Paint Techniques on the 0. 0175-Scale Model 56-Ots in the NASA/Ames Research Center 3. 5-Foot Hypersonic Wind Tunnel

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-08-06

Total Pages: 32

ISBN-13: 9781724694966

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An experimental investigation was performed in the NASA/Ames Research Center 3.5-foot Hypersonic Wind Tunnel to obtain supersonic heat-distribution data in areas between the orbiter and external tank using phase-change paint techniques. The tests used Novamide SSV Model 56-OTS in the first and second-stage ascent configurations. Data were obtained at a nominal Mach number of 5.3 and a Reynolds number per foot of 5 x 10 to the 6th power with angles of attack of 0 deg, +/- 5 deg, and sideslip angles of 0 deg and +/- 5 deg. Marroquin, J. Unspecified Center NASA-CR-167695, NAS 1.26:167695, DMS-DR-2524 NAS9-17179

Prediction Techniques for Pressure and Heat-Transfer Distributions Over Bodies of Revolution in High-Subsonic to Low-Supersonic Flight
Prediction Techniques for Pressure and Heat-Transfer Distributions Over Bodies of Revolution in High-Subsonic to Low-Supersonic Flight

Author: L. K. Isaacson

Publisher:

Published: 1968

Total Pages: 155

ISBN-13:

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A literature survey and an evaluation of applicable literature concerning pressure and heat-transfer distributions over bodies of revolution in high-subsonic to low-supersonic flight are presented. Methods for determining the pressure distribution on bodies of revolution are discussed and compared with experimental data. Variations of the modified Newtonian method may be applied to a large class of bodies of revolution for free-stream Mach numbers greater than 0.75. Appropriate experimental laminar and turbulent heat-transfer data for a blunt-body vehicle at flight Mach numbers between 1.6 and 5 are compared with calculated values. Experimental data could not be found for blunt-body turbulent heat transfer in the free-stream Mach number range from 0.7 to 1.6. An extensive bibliography covering prediction techniques and experimental data on pressure and heat-transfer distributions is included as the appendix. (Author).

Facing the Heat Barrier
Facing the Heat Barrier

Author: T.A. Heppenheimer

Publisher: Courier Dover Publications

Published: 2018-09-12

Total Pages: 355

ISBN-13: 0486834514

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This volume from The NASA History Series presents an overview of the science of hypersonics, the study of flight at speeds at which the physics of flows is dominated by aerodynamic heating. The survey begins during the years immediately following World War II, with the first steps in hypersonic research: the development of missile nose cones and the X-15; the earliest concepts of hypersonic propulsion; and the origin of the scramjet engine. Next, it addresses the re-entry problem, which came to the forefront during the mid-1950s, showing how work in this area supported the manned space program and contributed to the development of the orbital shuttle. Subsequent chapters explore the fading of scramjet studies and the rise of the National Aerospace Plane (NASP) program of 1985–95, which sought to lay groundwork for single-stage vehicles. The program's ultimate shortcomings — in terms of aerodynamics, propulsion, and materials — are discussed, and the book concludes with a look at hypersonics in the post-NASP era, including the development of the X-33 and X-34 launch vehicles, further uses for scramjets, and advances in fluid mechanics. Clearly, ongoing research in hypersonics has yet to reach its full potential, and readers with an interest in aeronautics and astronautics will find this book a fascinating exploration of the field's history and future.