Download or read book Experimental Investigation of Boundary Layer Transition on a Wedge at Mach 3 written by Vincent Perpoint and published by . This book was released on 1997 with total page 210 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Laminar Transitional and Turbulent Boundary layer Profiles on a Wedge at Local Mach Number 6 5 and Comparisons with Theory written by Michael C. Fischer and published by . This book was released on 1971 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel investigation of laminar, transitional, and turbulent boundary layer profiles on wedge at hypersonic speed to confirm theoretical analysis.
Download or read book Experimental Investigation of Boundary layer Transition on a Cooled 7 5 Total angle Cone at Mach 10 written by Philip E. Everhart and published by . This book was released on 1967 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of the Effect of Mass Transfer on a Wedge Induced Laminar Separated Boundary Layer at Mach 12 written by Karlheinz O. W. Ball and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of a Turbulent Boundary Layer at Mach 6 High Reynolds Numbers and Zero Heat Transfer written by Jerry B. Adcock and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Turbulent Step induced Boundary layer Separation at Mach Numbers 2 5 3 and 4 written by Jerry S. Hahn and published by . This book was released on 1969 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of turbulent separated boundary-layer flow was conducted using high forward-facing steps (with side plates) mounted on a flat plate at zero angle of attack. The tests were made at Mach numbers of 2.5, 3.0, and 4.0 for Reynolds numbers, based on the boundary-layer total thickness at the separation location, from 100,000 to 150,000. The effects of Mach number, step height and span, end plates, and step-face fairings were investigated. Data are presented graphically and in tabulations and include model surface pressures on the flat plate and on the face and top of selected steps, boundary-layer Mach number profiles, and selected oil dot photographs. (Author).
Download or read book Experimental Investigation of a Turbulent Boundary Layer at Mach 6 High Reynolds Numbers and Zero Heat Transfer written by Jerry B. Adcock and published by . This book was released on 1965 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental and Numerical Investigation of Boundary layer Development and Transition on the Walls of a Mach 5 Nozzle written by William D. Harvey and published by . This book was released on 1975 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of the Turbulent Boundary Layer at High Reynolds Numbers and a Mach Number of 0 8 written by L. Gaudet and published by . This book was released on 1984 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Separation Studies for Two dimensional Wedges and Curved Surfaces at Mach Numbers of 4 8 to 6 2 written by James R. Sterrett and published by . This book was released on 1962 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Boundary Layer Flow written by L. F. G. Simmons and published by . This book was released on 1935 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of a Hypersonic Glider Configuration at a Mach Number of 6 and at Full scale Reynolds Numbers written by Alvin Seiff and published by . This book was released on 1961 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Laminar Transitional and Turbulent Boundary layer Profiles on a Wedge at Local Mach Number 6 5 and Comparisons with Theory written by Michael C. Fischer and published by . This book was released on 1971 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An experimental investigation of the turbulent boundary layer behind a forward facing step in supersonic flow written by Dave Robert Moore and published by . This book was released on 1958 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the results of an experimental study of the effect of a disturbance, produced by a forward facing step, on the turbulent boundary layer in compressible flow. Boundary layer total pressure surveys and direct skin friction measurements were made at six stations on each of two test surfaces. One surface was smooth and the other surface had an 0.080-inch forward facing step. The test stations were all located downstream of the step, the height of which was approximately one-half the smooth surface boundary layer thickness. Data were obtained at Mach Numbers of 2.0, 2.5, 3.0, and 3.5 and the test Reynolds Numbers, based on momentum thickness, ranged from 8,000 to 10,000 approximately. The results of this investigation indicate that the effect of the disturbance, produced by the step on the 'law of the wall' and 'velocity defect law' profiles appears to be negligible from a point approximately 10 flat plate boundary layer thicknesses downstream from the step. (Author).
Download or read book Experimental Investigation of the Turbulent Boundary Layer on a Flat Plate with Zero Pressure Gradient at Mach Number written by David Ross Lane and published by . This book was released on 1953 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Turbulent Separated Boundary Layers at Low Supersonic Mach Numbers written by Robert E. Wilson and published by . This book was released on 1970 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Turbulent Boundary Layers with Pressure Gradient and Heat Transfer at Mach Number 4 written by J. S. Hahn and published by . This book was released on 1971 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the behavior of a turbulent boundary layer subjected to adverse and favorable pressure gradients was conducted at Mach number 4 for a free-stream Reynolds number of 0.500,000 per inch. Two severe pressure gradients were imposed on the boundary layer by interchangeable contoured centerbodies inside a large hollow cylinder for cold-wall and adiabatic-wall temperature conditions. Imposition of either of the adverse pressure gradients significantly decreased the natural growth rate of the boundary-layer displacement thickness, whereas the favorable pressure gradient had opposite effects; momentum thickness was relatively unaffected by pressure gradient. A pressure gradient increase of about 30 percent caused relatively small changes in the skin friction, heat-transfer rate, and the characteristic boundary-layer parameters. Wall cooling effects (T sub w/t sub 0 approximately 0.3) on the boundary-layer thickness parameters were nearly insignificant, in comparison with the adiabatic-wall results. Heat-transfer distributions were similar to the local skin friction results based on free-stream conditions. (Author).
