Download or read book Laminar Boundary layer Separation on Flared Bodies at Supersonic and Hypersonic Speeds written by J. Don Gray and published by . This book was released on 1965 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments at supersonic speeds and at Mach 8 were conducted to determine the conditions which govern the extent of shock-induced laminar flow separations on axisymmetric configurations at zero yaw and without heat transfer. From an extensive correlation of surface pressure data and schlieren photographs, it is shown that the extent of reverse flow is essentially a function of the ratio of the wetted length to the flare divided by the laminar boundary thickness there. As a result, the relative extent of laminar flow separation decreases with a unit Reynolds number increase and grows through an increase in Mach number. Finally, increasing the flare angle increases the length of the reverse flow region.
Download or read book Laminar Boundary layer Separation and Near wake Flow for a Smooth Blunt Body at Supersonic and Hypersonic Speeds written by Jean-Marie Grange and published by . This book was released on 1966 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Hypersonic Flow Separation and Its Effects on Aerodynamic Control Characteristics written by Douglas Eugene Abbott and published by . This book was released on 1962 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of the present study is to investigate laminar separation at hypersonic speeds, especially as it affects aerodynamic control characteristcis. Theoretical methods for use with computing machines hae been developed for calculating the pressure distribution due to laminar separation of the free-interaction type upstream and downstream of the separation point. The theories account for effects of Mach number, Reynolds number, wall heating and cooling, and specific heat ratio and show significant effects of all these parameters on separation. An experimental investigation was made of flare-cylinder combination with extensive separation at Mach numbers 4 and 6, Reynolds numbers of 10(3) to 10(4), and for adiabatic and cooled walls. In general, the separation was not of the free-interaction type so that modifications of the theory are required to adapt it to this type of separation. Methods for making such modifications are discussed together with methods for computing hypersonic control characteristics for various cases of seaparated flows.
Download or read book Supersonic Separated Flows Over Wedges and Flares with Emphasis on a Method of Detecting Transition written by Jean J. Ginoux and published by . This book was released on 1968 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The investigation is a first step to the study of the effect of cross flow in laminar separation at supersonic speeds. It is related to the selection of a final axi-symmetric model. Several problems were examined. First, the effect of streamwise vortices that develop systematically in laminar reattaching flows, triggered by small irregularities in the leading edge thickness. Second, the choice of the diameter of the model such that the flow resembles that of an equivalent planar body, third the programming of Lees-Reeves theory on a 1130 IBM computer to perform a parametric study and finally the development of a new accurate technique or criteria to ascertain that fully laminar shock wave boundary layer interactions can be obtained. (Author).
Download or read book Laminar Separation in Supersonic and Hypersonic Flows written by Jean J. Ginoux and published by . This book was released on 1965 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: High speed two-dimensional reattaching flows are characterized by the development of regularly spaced vortices in the boundary layer, whose effect is to produce heat transfer rates at reattachment which are, locally over the span, considerably higher in laminar and transitional flows than in the turbulent case. These results are expected to occur both at supersonic and hypersonic speeds, as these vortices were observed over a range of Mach numbers of 1.5 to 7.0. A basic difference in the recovery of total energy at reatachment was observed between laminar and transitional flows over ramps. In the latter case, the recovery temperature was maximum at reattachment and decreased to the laminar theoretical value in a region downstream of reattachment, where the flow was turbulent. The aerodynamic heating of sweptback wings can be predicted by a simple method derived from flat plate theory and by superimposing flow components parallel and perpendicular to the leading edge. Streamwise vortices do not seem to affect the average heat transfer coefficient. (Author).
Download or read book NASA Technical Note written by and published by . This book was released on 1968 with total page 466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Attached and Separated Boundary Layers on Highly Cooled Ablating and Nonablating Models at M written by Donald M. Kuehn and published by . This book was released on 1967 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1967 with total page 2300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for 1966 written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1967 with total page 2084 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Real gas Study of Low density Wedge induced Laminar Separation on a Highly Cooled Blunt Flat Plate at M infinity written by John Benjamin Anders and published by . This book was released on 1968 with total page 42 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 1972 with total page 1038 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1960 with total page 450 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 1965 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Heat Transfer Course Lecture Notes on Interference Flows written by Gerald L. Burke and published by . This book was released on 1972 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 684 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Separated Flows written by and published by . This book was released on 1966 with total page 270 pages. Available in PDF, EPUB and Kindle. Book excerpt:
