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Heat Transfer And Pressure Distributions At A Mach Number Of 6 For 70 Swept Slab Wings With Sharp And Spherical Noses And Cylindrical Leading Edges
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Book Synopsis Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges by :
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges by : Robert A. Jones
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by Robert A. Jones and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1966 with total page 468 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Distributions on 60 ̊and 70 ̊swept Delta Wings Having Turbulent Boundary Layers by : William M. Murray (Jr.)
Download or read book Heat-transfer and Pressure Distributions on 60 ̊and 70 ̊swept Delta Wings Having Turbulent Boundary Layers written by William M. Murray (Jr.) and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Distribution on 700 Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 900 by : Philip E. Everhart
Download or read book Heat-transfer Distribution on 700 Swept Slab Delta Wings at a Mach Number of 9.86 and Angles of Attack Up to 900 written by Philip E. Everhart and published by . This book was released on 1964 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer distributions were obtained on 700 swept slab delta wings with sharp and blunt noses and cylindrical leading edges. The free-stream Reynolds number based on model thickness was 9 x 10(4). Lees' theory for the heat-transfer distribution is shown to be in good agreement with the data obtained on the nose and leading edge. The point of peak heating on the leading edge is in close agreement with the Newtonian stagnation point at all angles of attack. At angles of attack from 40° to 60° cross-flow theory was in excellent agreement with experimental center-line data; however, at other model attitudes the theory differed significantly from experiment. Nose blunting resulted in reduced heating rates over the aft center-line section of the wing at angles of attack less than about 40°.
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 1964 with total page 1114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1964 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluation of Active Cooling Systems for a Mach 6 Hypersonic Transport Airframe by : R. G. Helenbrook
Download or read book Evaluation of Active Cooling Systems for a Mach 6 Hypersonic Transport Airframe written by R. G. Helenbrook and published by . This book was released on 1971 with total page 924 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transpiration and convective cooling concepts are examined for the fuselage and tail surface of a Mach 6 hypersonic transport aircraft. Hydrogen, helium, and water are considered as coolants. Heat shields and radiation barriers are examined to reduce heat flow to the cooled structures. The weight and insulation requirements for the cryogenic fuel tanks are examined so that realistic totals can be estimated for the complete fuselage and tail. Structural temperatures are varied to allow comparison of aluminum alloy, titanium alloy, and superalloy construction materials. The results of the study are combined with results obtained on the wing structure, obtained in a previous study, to estimate weights for the complete airframe. The concepts are compared among themselves, and with the uncooled concept on the basis of structural weight, cooling system weight, and coolant weight.
Book Synopsis Heat-transfer and Pressure Investigation of a Fin-plate Interference Model at a Mach Number of 6 by : Robert A. Jones
Download or read book Heat-transfer and Pressure Investigation of a Fin-plate Interference Model at a Mach Number of 6 written by Robert A. Jones and published by . This book was released on 1964 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 40th AIAA Aerospace Sciences Meeting & Exhibit by :
Download or read book 40th AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2002 with total page 708 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design and Evaluation of Active Cooling Systems for Mach 6 Cruise Vehicle Wings by : W. A. McConarty
Download or read book Design and Evaluation of Active Cooling Systems for Mach 6 Cruise Vehicle Wings written by W. A. McConarty and published by . This book was released on 1971 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt: Active cooling systems, which included transpiration, film, and convective cooling concepts, are examined. Coolants included hydrogen, helium, air, and water. Heat shields, radiation barriers, and thermal insulation are considered to reduce heat flow to the cooling systems. Wing sweep angles are varied from 0 deg to 75 deg and wing leading edge radii of 0.05 inch and 2.0 inches are examined. Structural temperatures are varied to allow comparison of aluminum alloy, titanium alloy, and superalloy structural materials. Cooled wing concepts are compared among themselves, and with the uncooled concept on the basis of structural weight, cooling system weight, and coolant weight.
Author :United States. National Aeronautics and Space Administration Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :1152 pages Book Rating :4.F/5 ( download)
Book Synopsis NASA Scientific and Technical Reports by : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1965 with total page 1152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :United States. National Aeronautics and Space Administration. Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :1156 pages Book Rating :4.E/5 ( download)
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1964 with total page 1156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Battelle Technical Review by : Battelle Memorial Institute
Download or read book Battelle Technical Review written by Battelle Memorial Institute and published by . This book was released on 1963 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Jet Propulsion written by and published by . This book was released on 1961 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: Beginning Oct. 1959 some issues include "Russian supplement."
Download or read book NASA SP. written by and published by . This book was released on 1965 with total page 1150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6 by : Louis G. Kaufman
Download or read book Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6 written by Louis G. Kaufman and published by . This book was released on 1979 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
