Download or read book Heat Transfer Tests of Two Space Shuttle Orbiter Configurations at Mach Number 8 written by W. R. Martindale and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer tests were conducted on two Space Shuttle configurations at Mach number 8 to investigate the effects of nose geometry on windward and leeward heating and boundary layer transition. Free-stream Reynolds number based on model length was varied from 1.5 to 7.5 million at angles of attack from 20 to 50 deg. Windward centerline heating rates were in general agreement with calculated values except for laminar rates dowstream of the wing/body junction. Differences in the location of the beginning of transition and the length of the transition zone were observed for the two configurations, but it was not clear whether variation in nose shape per se or the abrupt cross-sectional change from the nose to the aft fuselage and wing was the controlling factor. (Author).

Download or read book Heat Transfer Tests of the NASA Rockwell International Space Shuttle Orbiter OH 84B IH 102 and OH 105 written by K. W. Nutt and published by . This book was released on 1979 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer tests were conducted on two 0.0175 scale and one 0.04 scale models of the space shuttle orbiter using the thin-skin thermocouple technique. Data were recorded at Mach numbers 3 and 4 in the AEDC-VKF Supersonic Wind Tunnel A and at Mach 8 in the Hypersonic Tunnel B. Ten model configurations were tested including each orbiter model and the two 0,0175 scale models integrated with the external tank and both solid rocket boosters. The objective of the test was to obtain heating data in regions of the orbiter where no previous data exist or where data extrapolation was not feasible. The model angle of attack ranged from -40 to 40 degrees with yaw angles varying from -15 to 10 degrees. (Author).

Download or read book Heat transfer and Flow field Tests of the North American Rockwell General Dynamics Convair Space Shuttle Configurations written by W. R. Martindale and published by . This book was released on 1973 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerothermodynamic tests of Phase B space shuttle configurations proposed by North American Rockwell/General Dynamics Convair were conducted at Mach number 8. Test conditions provided both Mach number and Reynolds number simulation for typical ascent and reentry trajectories. This report provides a comprehensive analysis of the major test results and also presents data comparisons with theoretical calculations. Specific areas covered are: ascent heating and shock interference, booster reentry heating and flow fields, and orbiter reentry including leeside heating, windward shock angles and flow fields, windward surface heating, and boundary-layer transition.

Download or read book Heat Transfer Tests on the Rockwell International Space Shuttle Orbiter with Boundary Layer Trips OH 54 written by D. B. Carver and published by . This book was released on 1976 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerothermodynamic transition tests on a model of the forward half of the Rockwell International Space Shuttle Orbiter Configuration 140C were conducted at Mach Number 8. Phase-change paint was used to determine the aerodynamic heating rates on the windward side of Orbiter models during simulated atmospheric reentry. The majority of the data was obtained using spherical trip elements of varying sizes at three different axial stations along the model to determine the effect of roughness size and location on boundary- layer transition. Additional data were taken with models which had scale indentations that simulated external tank attachment rings, nose wheel well doors, and a surface insulation interface gap. Data were taken over an angle-of-attack range from 20 to 40 deg at free-stream Reynolds numbers, based on the total Orbiter scaled length, from 3.2 to 16.1 million. Typical heat-transfer data were presented to illustrate boundary-layer transition locations and sensitivities to test variables.

Download or read book Heat transfer and Flow field Tests of the McDonnell Douglas Martin Marietta Space Shuttle Configurations written by Richard K. Matthews and published by . This book was released on 1973 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerothermodynamic tests of Phase B space shuttle configurations proposed by McDonnell Douglas--Martin Marietta were conducted at Mach numbers 8 and 10.5. Test conditions provided both Mach number and Reynolds number simulation for typical ascent and reentry trajectories. This report provides a comprehensive analysis of the major test results and also presents data comparisons with theoretical calculations. Specific areas covered are ascent heating and shock interference, booster reentry heating and flow fields, and orbiter reentry analysis which includes leeside heating, windward shock angles and flow fields, windward surface heating, and boundary-layer transition.

Download or read book Heat Transfer Tests on the Rockwell International Space Shuttle Orbiter with and Without Simulated Protuberances written by L. D. Carter and published by . This book was released on 1975 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerothermodynamic tests on the forward half of the Rockwell International Space Shuttle Orbiter Configuration 140C were conducted at Mach number 8. The phase-change paint and thin-skin thermocouple techniques were used to determine the aerodynamic heating rates on the Orbiter models during simulated atmospheric reentry. Smooth 0.04-scale models and models with scaled protuberances and indentations which simulated the windshields, cargo bay door hinges, vents, and thruster nozzles were tested over an angle-of-attack range from 20 to 45 deg at yaw angles from -5 to 5 deg and at Reynolds numbers, based on the total Orbiter scaled length, from 2.15 to 15.9 million. Comparisons of the model heat-transfer rates obtained with a smooth surface and with scaled protuberances are presented.

Download or read book Heat Transfer Test on the NASA Rockwell International Space Shuttle Orbiter at Mach Number 8 0 in AEDC VKF Tunnel B written by E. C. Knox and published by . This book was released on 1978 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer data were obtained on a 0.0175-scale and on a 0.04-scale model of the NASA/Rockwell International Space Shuttle Orbiter. The data were obtained at mach 8 in the AEDC/VKF Tunnel B at angles of attack from 25 to 42.5 deg and at several free-stream Reynolds numbers from 500,000 to 3,700,000 per ft. (Author).

Download or read book Heat Transfer Tests of a 0 0175 Scale Model of the Space Shuttle at Mach Numbers 2 5 3 5 4 5 and 5 5 written by K. W. Nutt and published by . This book was released on 1976 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer tests were conducted on the Space Shuttle Integrated Vehicle to investigate heat-transfer rates during the ascent phase of the flight profile. The model was a 0.0175-scale, thin skin, thermocouple-equipped model (60-OTS) of the Rockwell International Vehicle 5 configuration. The tests were conducted at nominal Mach numbers of 2.5, 3.5, 4.5, and 5.5 and a free-stream unit Reynolds of 5 million per foot. Two nose configurations were tested on the external tank. Data were obtained with the external tank alone and with the external tank and solid rocket booster in the integrated vehicle configuration. This report presents representative test results and data comparisons with theoretical calculations. (Author).

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1972 with total page 958 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Download or read book Shock interference heat transfer to tank configurations mated to a straight wing space shuttle orbiter at Mach number 10 3 written by Davis H. Crawford and published by . This book was released on 1976 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Annual Index written by and published by . This book was released on 1975 with total page 882 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Rockwell International Space Shuttle Orbiter Yaw Heating Test OH 109 written by K. W. Nutt and published by . This book was released on 1981 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Thin-skin thermocouple heat transfer tests were conducted on two 0.0175 scale and one 0.04 scale model of the space shuttle orbiter. In addition, a phase-change paint heat transfer test was conducted on a 0.0175 scale SILTS Pod tail of the orbiter. Oil flow data were also obtained on the orbiter's upper surface. The primary objective of the thin skin thermocouple entry was to obtain better identification of regions of peak heating on the upper surface of the orbiter with attention to the Orbiter Maneuvering System (OMS) pods. The objective of the phase-change paint entry was to establish the peak heating location on the orbiter SILTS tail configuration. Data were recorded at Mach 8 in the AEDC-VKF Hypersonic Wind Tunnel B at free stream Reynolds numbers ranging from 500,000 to 3,700,000. The model angle of attack ranged from 20 to 40 degrees with yaw angle varying from -2 to 2 degrees. (Author).

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1988 with total page 1142 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Roughness and Wall Temperature Effects on Boundary Layer Transition on a 0 0175 Scale Space Shuttle Orbiter Model Tested at Mach Number 8 written by G. D. Wannenwetsch and published by . This book was released on 1977 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer tests were conducted on the Space Shuttle Orbiter Vehicle in the AEDC/VKF Hypersonic Wind Tunnel (B) to determine the location of boundary-layer transition for a simulated reentry phase flight profile. The model was a 0.0175-scale model with simulated randomly misaligned thermal protection system tiles etched into the windward surface. The tests were conducted at a nominal free-stream Mach number of 8, free-stream unit Reynolds numbers ranging from 0.5 million to 3.7 million per ft, and angles of attack of 30, 35, and 40 deg. Values of wall temperature to free-stream stagnation temperature ranged from 0.14 to 0.44. Representative test data and an analysis of the windward surface centerline heat-transfer data are included. Effects of wall temperature, tile roughness, and angle of attack on the location of transition are discussed.

Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1979 with total page 752 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements written by and published by . This book was released on 1974 with total page 1000 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Documentation and Archiving of the Space Shuttle Wind Tunnel Test Data Base Volume 1 Background and Description written by and published by . This book was released on 1995 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt: