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:
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).
Download or read book The High Temperature Aspects of Hypersonic Flow written by Wilbur C. Nelson and published by Elsevier. This book was released on 2014-12-02 with total page 801 pages. Available in PDF, EPUB and Kindle. Book excerpt: The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page 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 1962 with total page 1116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Pressure Distributions on Reentry Nose Shapes at a Mach Number of 3 55 written by Warren A. Lawson and published by . This book was released on 1960 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measurements of the Surface Flows Heat Transfer Pressure Distribution and Longitudinal Stability of a Mercury Capsule Model at Mach Numbers of 6 9 and 9 6 written by Philip E. Everhart and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Reports written by and published by . This book was released on 1961 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure and Heat transfer Distribution on the Afterbody of a Lifting Mercury type Capsule at Mach Number 15 in Helium written by Joseph G. Marvin and published by . This book was released on 1963 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1974 with total page 992 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Aerothermodynamics written by and published by . This book was released on 1984 with total page 344 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Surface Pressures and Heat Transfer on Unswept Blunt Plates in Helium at High Mach Numbers written by Joseph G. Marvin and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Transfer to the Conical Afterbody of a Blunt nosed Reentry Body with Various Nose edge Radii at Mach 6 written by and published by . This book was released on 1965 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Transfer and Pressure Measurement on a 5 inch Hemispherical Concave Nose at a Mach Number of 2 0 written by J. Thomas Markley and published by . This book was released on 1958 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The concave-nose stagnation-point heating is 40 percent of that of a hemisphere nose shape having the same diameter. At angles of attack of ℗±5© and ℗± 10© there is no increase in heating of the nose. Total pressures behind the shock were experienced up to 60© on the concave part for all angles of attack. The tests were made under sea-level conditions for a Reynolds number per foot of about 14 x 106.
Download or read book Local Heat Transfer to Blunt Noses at High Supersonic Speeds written by William E. Stoney and published by . This book was released on 1957 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Optimum Shape for Transpiration cooled Nosetip of a Re entry Vehicle written by Kevin E. Yelmgren and published by . This book was released on 1978 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: The variations of parameters method was used to determine the optimum nose shape for a reentry vehicle having a transpiration-cooled nosetip (TCNT). Three families of nose shapes were considered - The oblate ellipsoid, the flat face - round shoulder, and the spherical arc - round shoulder. These families are bounded by the flat face - sharp corner at one extreme and the hemisphere at the other extreme. The amount of coolant required by each nose shape during reentry was determined by using a high speed computer to couple the aerodynamic equations with the trajectory equations. The optimum shape is the shape which requires the least amount of coolant for reentry. The flat face - sharp corner shape was found to require the least amount of coolant, about 60 percent less water than the hemisphere. Although the time to impact is longer for the flat face, the smaller surface area and lower heating intensity more than offsets the increased reentry time. The possibility of an optimum flat face height was also investigated; no face height was found that minimized the total heating to the vehicle during reentry. (Author).
Download or read book Pressure Distribution at a Mach Number of 24 5 on a Symmetrical Blunt faced Reentry Body at Angles of Attack from 0 Deg to 40 Deg in Helium Including an Investigation of Afterbody Sting Effects written by and published by . This book was released on 1963 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
