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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...
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 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 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 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 1994 with total page 892 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:
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:
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 Government Reports Annual Index by :
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:
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 Laminar Heat-transfer and Pressure-distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium by : Richard D. Wagner
Download or read book Laminar Heat-transfer and Pressure-distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium written by Richard D. Wagner and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Use of Nose Cap and Fuselage Pressure Orifices for Determination of Air Data for Space Shuttle Orbiter Below Supersonic Speeds by : Terry J. Larson
Download or read book Use of Nose Cap and Fuselage Pressure Orifices for Determination of Air Data for Space Shuttle Orbiter Below Supersonic Speeds written by Terry J. Larson and published by . This book was released on 1980 with total page 132 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 Laminar Heat-transfer and Pressure-distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium by : RICHARD D. JR. WAGNER
Download or read book Laminar Heat-transfer and Pressure-distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium written by RICHARD D. JR. WAGNER and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the 2-in. helium tunnel at the Langley Research Center at a Mach number of 19.4 to determine the pressure distributions and heat-transfer characteristics of a family of reentry nose shapes. The pressure and heat-transfer-rate distributions on the nose shapes are compared with theoretical predictions to ascertain the limitations and validity of the theories at hypersonic speeds. The experimental results were found to be adequately predicted by existing theories. Two of the nose shapes were tested with variable-length flow-separation spikes. The results obtained by previous investigators of spike-nose bodies were found to prevail at the higher Mach number of the present investigation. (Author).
Book Synopsis Experimental Pressure Distributions on a Blunt Lifting-entry Body at Mach 3.71 by : W. Douglas Morris
Download or read book Experimental Pressure Distributions on a Blunt Lifting-entry Body at Mach 3.71 written by W. Douglas Morris and published by . This book was released on 1968 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Induced-pressure Phenomena on Axially Symmetric, Flow-alined, Cylindrical Models Equipped with Different Nose Shapes at Free-stream Mach Numbers from 15.6 to 21 in Helium by : James N. Mueller
Download or read book An Investigation of Induced-pressure Phenomena on Axially Symmetric, Flow-alined, Cylindrical Models Equipped with Different Nose Shapes at Free-stream Mach Numbers from 15.6 to 21 in Helium written by James N. Mueller and published by . This book was released on 1960 with total page 52 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 199? with total page 880 pages. Available in PDF, EPUB and Kindle. Book excerpt:
