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Pressure Distributions Obtained On A 004 Scale And 002 Scale Model Of The Space Shuttle Orbiters Forward Fuselage In The Langley Continuous Flow Hypersonic Tunnel
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Book Synopsis Pressure Distributions Obtained on a 0.04-scale and 0.02-scale Model of the Space Shuttle Orbiter's Forward Fuselage in the Langley Continuous Flow Hypersonic Tunnel by :
Download or read book Pressure Distributions Obtained on a 0.04-scale and 0.02-scale Model of the Space Shuttle Orbiter's Forward Fuselage in the Langley Continuous Flow Hypersonic Tunnel written by and published by . This book was released on 1983 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions Obtained on a 0.04-scale and 0.02-scale Model of the Space Shuttle Orbiter's Forward Fuselage in the Langley 20-inch Mach 6 Air Tunnel by :
Download or read book Pressure Distributions Obtained on a 0.04-scale and 0.02-scale Model of the Space Shuttle Orbiter's Forward Fuselage in the Langley 20-inch Mach 6 Air Tunnel written by and published by . This book was released on 1983 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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...
Book Synopsis Interference Problems on Wing-fuselage Combinations in Inviscid, Incompressible Flow by : Aeronautical Research Council (Great Britain)
Download or read book Interference Problems on Wing-fuselage Combinations in Inviscid, Incompressible Flow written by Aeronautical Research Council (Great Britain) and published by . This book was released on 1974 with total page 1212 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions Obtained on a 0.10-scale Model of the Space Shuttle Orbiter's Forebody in the Ames Unitary Plan Wind Tunnel by :
Download or read book Pressure Distributions Obtained on a 0.10-scale Model of the Space Shuttle Orbiter's Forebody in the Ames Unitary Plan Wind Tunnel written by and published by . This book was released on 1986 with total page 490 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1983 with total page 1096 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index: Keyword A-L by :
Download or read book Government Reports Annual Index: Keyword A-L written by and published by . This book was released on 1983 with total page 1092 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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
Download or read book Comparison of Predicted and Experimental Real-gas Pressure Distributions on Space Shuttle Orbiter Nose for Shuttle Entry Air Data System written by Judy L. Shinn and published by . This book was released on 1980 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions on a 0.02-scale Space Shuttle Orbiter Nose at Mach 21.5 in Helium by : George C. Ashby (Jr.)
Download or read book Pressure Distributions on a 0.02-scale Space Shuttle Orbiter Nose at Mach 21.5 in Helium written by George C. Ashby (Jr.) and published by . This book was released on 1994 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Pressure Signatures for a 0.0041-scale Model of the Space Shuttle Orbiter by :
Download or read book Wind Tunnel Pressure Signatures for a 0.0041-scale Model of the Space Shuttle Orbiter written by and published by . This book was released on 1975 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lee-surface Heating and Flow Phenomena on Space Shuttle Orbiters at Large Angles of Attack and Hypersonic Speeds by : Jerry N. Hefner
Download or read book Lee-surface Heating and Flow Phenomena on Space Shuttle Orbiters at Large Angles of Attack and Hypersonic Speeds written by Jerry N. Hefner and published by . This book was released on 1972 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The lee-surface flow phenomena on a delta-wing orbiter and a straight-wing orbiter have been investigated at angles of attack between 0 deg and 50 deg at a Mach number of 6. Limited studies of the delta-wing orbiter were conducted at a Mach number of 19. Heat-transfer data, pressure distributions, and oil-flow studies were employed to experimentally examine the nature of the surface flow and the severity of the lee-surface heating. The effects of Reynolds number on the flow field and heating were investigated. Problem areas are defined and areas for further study are recommended.
Book Synopsis Pressure Distributions on a 0.02-scale Space Shuttle Orbiter Nose at Mach 21.5 in Helium by : George C. Ashby
Download or read book Pressure Distributions on a 0.02-scale Space Shuttle Orbiter Nose at Mach 21.5 in Helium written by George C. Ashby and published by . This book was released on 1994 with total page 73 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Further Wind Tunnel Measurements of Pressure Signatures for a 0.0041-scale Model of the Space Shuttle Orbiter by :
Download or read book Further Wind Tunnel Measurements of Pressure Signatures for a 0.0041-scale Model of the Space Shuttle Orbiter written by and published by . This book was released on 1976 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Surface Pressure Distributions on 0.0628-scale Models of Proposed Project Fire Space Vehicles at Mach Numbers from 0.25 to 4.63 by : Albin O. Pearson
Download or read book Surface Pressure Distributions on 0.0628-scale Models of Proposed Project Fire Space Vehicles at Mach Numbers from 0.25 to 4.63 written by Albin O. Pearson and published by . This book was released on 1963 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722722333 Total Pages :80 pages Book Rating :4.7/5 (223 download)
Book Synopsis Results of Experimental Investigations to Determine External Tank Protuberance Loads Using a 0.03-Scale Model of the Space Shuttle Launch Configuration (Model 47-Ots) in the Nasa/ARC Unitary Plan Wind Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book Results of Experimental Investigations to Determine External Tank Protuberance Loads Using a 0.03-Scale Model of the Space Shuttle Launch Configuration (Model 47-Ots) in the Nasa/ARC Unitary Plan Wind Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-13 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: Data were obtained on a 3-percent model of the Space Shuttle launch vehicle in the NASA/Ames Research Center 11x11-foot and 9x7-foot Unitary Plan Wind Tunnels. This test series has been identified as IA19OA/B and was conducted from 7 Feb. 1980 to 19 Feb. 1980 (IA19OA) and from 17 March 1980 to 19 March 1980 and from 8 May 1980 to 30 May 1980 (IA19OB). The primary test objective was to obtain structural loads on the following external tank protuberances: (1) LO2 feedline; (2) GO2 pressure line; (3) LO2 antigeyser line; (4) GH2 pressure line; (5) LH2 tank cable tray; (6) LO2 tank cable tray; (7) Bipod; (8) ET/SRB cable tray; and (9) Crossbeam/Orbiter cable tray. To fulfill these objectives the following steps were taken: Eight 3-component balances were used to measure forces on various sections of 1 thru 6 above; 315 pressure orifices were distributed over all 9 above items. The LO2 feedline was instrumented with 96 pressure taps and was rotated to four positions to yield 384 pressure measurements. The LO2 antigeyser line was instrumented with 64 pressure taps and was rotated to two positions to yield 128 pressure measurements; Three Chrysler miniature flow direction probes were mounted on a traversing mechanism on the tank upper surface centerline to obtain flow field data between the forward and aft attach structures; and Schlieren photographs and ultraviolet flow photographs were taken at all test conditions. Data from each of the four test phases are presented. Houlihan, S. R. Unspecified Center...
Book Synopsis Flow-field Surveys on the Windward Side of the NASA 040A Space Shuttle Orbiter at 31 ̊angle of Attack and Mach 20 in Helium by : George C. Ashby
Download or read book Flow-field Surveys on the Windward Side of the NASA 040A Space Shuttle Orbiter at 31 ̊angle of Attack and Mach 20 in Helium written by George C. Ashby and published by . This book was released on 1977 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
