Download or read book Local Aerodynamic Heat Transfer and Boundary layer Transition on Roughened Sphere ellipsoid Bodies at Mach Number 3 0 written by William D. Deveikis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Simplified Method for Determination of Critical Height of Distributed Roughness for Boundary layer Transition at Mach Numbers from 0 to 5 written by Albert L. Braslow and published by . This book was released on 1958 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt: The method has been applied to various types of configurations in several wind-tunnel investigations conducted by the National Advisory Committee for Aeronautics at Mach numbers up to 4, and in all cases the calculated roughness height caused premature boundary-layer transition for the range of test conditions.

Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1961 with total page 1878 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Heating and Boundary layer Transition on a 1 10 power Nose Shape in Free Flight at Mach Numbers Up to 6 7 and Free stream Reynolds Numbers Up to 16 X 10 6 written by Benjamine J. Garland and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Measurements of Aerodynamic Heat Transfer and Boundary Layer Transition on a 10 Deg Cone in Free Flight at Supersonic Mach Numbers Up to 5 9 written by Charles B. Rumsey and published by . This book was released on 1961 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Heat Transfer and Boundary layer Transition on Two Blunt Bodies at Mach Number 3 12 written by N. S. Diaconis and published by . This book was released on 1957 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local heat-transfer parameters were measured on a hemisphere-cone-cylinder and on a 120 degree-included-angle cone-cylinder at a free-stream Mach number of 3.12 and at free-stream unit Reynolds numbers as high as 1,292.000 per inch. Heat-transfer data are presented for the case of wall temperature approximat&ly equal to free-stream static temperature.

Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1961-10 with total page 1540 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Heat Transfer to Bodies at Angles of Attack written by William V. Feller and published by . This book was released on 1957 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Fixing Boundary layer Transition for a Swept and a Triangular wing and Body Combination at Mach Numbers from 0 60 to 1 40 written by Louis S. Stivers and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Variation of Boundary layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3 12 written by John R. Jack and published by . This book was released on 1955 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.

Download or read book Analysis of Boundary layer Transition on X 15 2 Research Airplane written by Albert L. Braslow and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1962 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Leading edge Effects on the Laminar Flat plate Boundary Layer and the Aerodynamic Heating at Mach 10 4 written by Howard W. Stone and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Mach Number and Wall temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5 written by Thorval Tendeland and published by . This book was released on 1959 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The heat-transfer data obtained from the model were found to correlate when the T' method of Sommer and Short was used. The increase in turbulent heat-transfer rate with a reduction in wall to free-stream temperature ratio was of the same order of magnitude as has been found for the turbulent skin-friction coefficient.

Download or read book Effects of Mach Number Leading Edge Bluntness and Sweep on Boundary layer Transition on a Flat Plate written by Don W. Jillie 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 Forced Boundary Layer Transition on X 43 Hyper X in NASA LaRC 20 Inch Mach 6 Air Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeroheating and boundary layer transition characteristics for the X-43 (Hyper-X) configuration have been experimentally examined in the Langley 20-Inch Mach 6 Air Tunnel. Global surface heat transfer distributions, and surface streamline patterns were measured on a 0.333-scale model of the Hyper-X forebody. Parametric variations include angles-of-attack of 0-deg, 2-deg, and 4-deg; Reynolds numbers based on model length of 1.2 to 15.4 million; and inlet cowl door both open and closed. The effects of discrete roughness elements on the forebody boundary layer, which included variations in trip configuration and height, were investigated. This document is intended to serve as a release of preliminary data to the Hyper-X program; analysis is limited to observations of the experimental trends in order to expedite dissemination.Berry, Scott A. and DiFulvio, Michael and Kowalkowski, Matthew K.Langley Research CenterAERODYNAMIC HEATING; BOUNDARY LAYER TRANSITION; WIND TUNNEL TESTS; SCALE MODELS; HEAT TRANSFER; HYPERSONIC FLIGHT; THERMOGRAPHY; ANGLE OF ATTACK; REYNOLDS NUMBER; HYPERSONIC SPEED; X-43 VEHICLE