Download or read book Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1961 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.

Download or read book An Investigation of the Effects of Heat Transfer on Boundary layer Transition of a Parabilic Body of Revolution NACA RM 10 at a Mach Number of 1 61 written by K.R. Czarnecki and published by . This book was released on 1955 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book AN EXTENSION OF THE EFFECTS OF HEAT TRANSFER ON BOUNDARY LAYER TRANSITION ON A PARABOLIC BODY OF REVOLUTION NACA RM 10 AT A MACH NUMBER OF 1 61 written by and published by . This book was released on 1954 with total page 25 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 1956 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1959 with total page 388 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 1954 with total page 910 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1954 with total page 938 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book WADC Technical Note written by United States. Wright Air Development Division and published by . This book was released on 1959 with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Boundary Layer Theory written by Hermann Schlichting and published by . This book was released on 1960 with total page 684 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 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index to Current Technical Literature written by and published by . This book was released on 1954-06 with total page 1084 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Studies written by Zbiginew Krzywoblocki and published by . This book was released on 1957 with total page 266 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 1963 with total page 1220 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1956 with total page 1174 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book High Speed Aerodynamics and Jet Propulsion Turbulent flows and heat transfers C C Lin written by Chia-Chʻiao Lin and published by . This book was released on 1959 with total page 582 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report written by and published by . This book was released on 1955 with total page 992 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Variation with Reynolds Number of the Base Wave and Skin friction Drag of a Parabolic Body of Revolution NACA RM 10 at Mach Numbers of 1 62 1 93 and 2 41 in the Langley 9 inch Supersonic Tunnel written by Eugene S. Love and published by . This book was released on 1952 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: