Download or read book The Application of a Nonsimilar Laminar Boundary Layer Analysis to Hypersonic Inlet Compression Surfaces written by Dennis Sedlock and published by . This book was released on 1966 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the results of an investigation in which the Smith and Clutter nonsimilar laminar boundary layer analysis is compared to experimental data and a modified linearized similar solution on typical hypersonic two-dimensional and axisymmetric inlet compression surfaces. The representative cases presented have a Mach number range of 11.6 to 16.87 and a unit Reynolds number of 60,000 to 400,000. For these conditions on the models investigated, the nonsimilar solution was found to treat transverse curvature as a first rather than a second order effect. Such factors as the input nondimensional boundary layer thickness, the distance between stations along the surface, and the selection of reference conditions were found to have an effect on the accuracy of the solution. The method showed satisfactory agreement with experimental data and the modified similar solution. Although not prohibitively long, the length of computer time suggests that the program should be used as a final design analysis tool rather than being applied in preliminary design stages. The detailed output of various quantities in the viscous layer makes the program particularly useful where temperature and velocity profiles are required. (Author).
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 912 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 1979 with total page 1074 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers Data reduction program and tabulated experimental data written by J. F. Stroud and published by . This book was released on 1965 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.
Download or read book U S Government Research Development Reports written by and published by . This book was released on 1967 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1967 with total page 1352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Compilation of Computer Programs in Flight Vehicle Technology written by Ambrose B. Nutt and published by . This book was released on 1968 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt: A compilation of computer programs useful in the design of flight vehicles. Technical domains covered include the following: Structures; Aerodynamics; Vehicle dynamics; Flight control; Environmental control; Crew escape and retardation; and Landing gear subsystems. All programs were devised in-house in the Air Force Flight Dynamics Laboratory or were prepared for them under R and D contracts. (Author).
Download or read book An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers written by J. F. Stroud and published by . This book was released on 1965 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.
Download or read book Turbulent Boundary Layer Skin Friction Heat Transfer and Pressure Measurements on Hypersonic Inlet Compression Surfaces written by M. O Ryder (Jr) and published by . This book was released on 1968 with total page 143 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study of turbulent boundary layer flow, under the influence of adverse pressure gradients typical of hypersonic inlets, was conducted on a two-dimensional and an axisymmetric model each instrumented with skin friction, heat transfer and pressure gages. Tests were conducted over a Mach and Reynolds number rage of 6.74 to 11.37 and 1,050,000 per ft. to 29,300,000 per ft., respectively. These test conditions produced boundary layer transition on the forward portions of the models without resorting to artificial trips. It was possible to attain a fully turbulent boundary layer before the start of the adverse pressure gradient region for most of the axisymmetric model tests but for most of the two-dimensional tests, transition was not completed until after the start of the pressure gradient. A comparison of the pressure data with the inviscid pressure distribution was made and good agreement is generally found indicating very little change in effective model shape due to boundary layer growth. This result is a consequence of the large model size relative to the boundary layer thickness, i.e. high Reynolds number flows over large models. An important conclusion resulting from this program was that turbulent boundary layers can negotiate large adverse pressure gradients without separating. Comparison with some existing laminar boundary layer data indicate that a turbulent boundary layer can negotiate adverse pressure gradients at least an order of magnitude greater than those gradients which will separate a laminar layer. (Author).
Download or read book The Analysis of a Nonsimilar Laminar Boundary Layer written by Dennis Dale Stalmach and published by . This book was released on 1978 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1967 with total page 686 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 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Curved Compression Inlet and Its Inverse Design written by Kunyuan Zhang and published by Springer Nature. This book was released on 2020-01-22 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents systematic research results on curved shock wave-curved compression surface applied to the compression surface design of supersonic–hypersonic inlet, which is a brand new inlet design. The concept of supersonic inlet curved compression discussed originated from the author’s research at the Deutsches Zentrum fur Luft- und Raumfahrt (DLR SM-ES) in the early 1990s. This book introduces the research history, working characteristics, performance calculation and aerodynamic configuration design method of this compression mode in detail. It also describes method of estimating the minimum drag in inlet and drag reduction effect of curved compression and proposes a new index for evaluating unit area compression efficiency of the inlet. Further, it reviews the relevant recent research on curved compression. As such it is a valuable resource for students, researchers and scientists in the fields of hypersonic propulsion and aeronautics.
Download or read book Effect of Bluntness on Hypersonic Two dimensional Inlet Type Flows written by Robert J. Sanator and published by . This book was released on 1968 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Scientific and Technical Reports and Publications for 1969 A Selected Listing written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1970 with total page 956 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers written by John F. Stroud and published by . This book was released on 1965 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.
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 1970 with total page 966 pages. Available in PDF, EPUB and Kindle. Book excerpt:
