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 Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1960 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Free Flight Research Investigations of heat trasfer and aerodynamic stability by O R Burggraf written by and published by . This book was released on 1960 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Free flight Measurements of Heat Transfer and Transition on a 10 Cone Having a Low Temperature Ratio written by Charles F. Merlet and published by . This book was released on 1961 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obtained from a free-flight test of a 100-inch-long 10° total-angle cone with a 1/16-inch tip radius which penetrated deep into the region of infinite stability of laminar boundary layer over a range of wall-to-local-stream temperature radius and for local Mach numbers from 1.8 to 3.5. Experimental heat-transfer coefficients, obtained at Reynolds numbers up to 160 x 106, were in general somewhat higher than theoretical values. A maximum Reynolds number of transition of only 33 x 106 was obtained. Contrary to theoretical and some other experimental investigations, the transition Reynolds number initially increased while the wall temperature ratio increased at relatively constant Mach number. Further increases in wall temperature ratio were accompanied by a decrease in transition Reynolds number. Increasing transition Reynolds number with increasing Mach number was also indicated at a relatively constant wall temperature ratio.
Download or read book Measurements of Heat Transfer Rates and Boundary Layer Transition on a Blunt nosed Body of Revolution in Free flight at Supersonic and Hypersonic Speeds written by A. Naysmith and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Review of High speed Convective Heat transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transition Fixing for Hypersonic Flow written by and published by . This book was released on 1967 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Influence of Free stream Disturbances on Boundary layer Transition written by William D. Harvey and published by . This book was released on 1978 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Comments on Hypersonic Boundary layer Transition written by Kenneth F. Stetson and published by . This book was released on 1990 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
Download or read book Hypersonic Boundary Shear Layer Transition for Blunt to Slender Configurations A NASA Langley Experimental Perspective written by and published by . This book was released on 2004 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Some Heat Transfer Problems in Hypersonic Flow written by Antonio Ferri and published by . This book was released on 1959 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Boundary Layer Transition Experiments written by Kenneth F. Stetson and published by . This book was released on 1980 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures written by Ernst Rudolf Georg Eckert and published by . This book was released on 1960 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Influence of Free stream Disturbances on Boundary layer Transition written by Bill Harvey and published by . This book was released on 1978 with total page 40 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 Degree 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 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Free flight Measurement of Heat Transfer and Transition on a 10 Degree Cone Having a Low Temperature Ratio written by Charles F. Merlet and published by . This book was released on 1957 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obtained from a free-flight test of a 100-inch-long 10 degree total-angle cone with a 1/16-inch tip radius which penetrated deep into the region of infinite stability of laminar boundary layer over a range of wall-to-local-stream temperature ratios and for local Mach numbers from 1.8 to 3.5. Experimental heat-transfer coefficients, obtained at Reynolds numbers up to 160,000,000, were in general somewhat higher than theoretical values. A maximum Reynolds number of transition of only 33,000,000 was obtained. Contrary to theoretical and some other experimental investigations, the transition Reynolds number initially increased while the wall temperature ratio increased at relatively constant Mach number. Further increases in wall temperature ratio were accompanied by a decrease in transition Reynolds number. Increasing transition Reynolds number with increasing Mach number was also indicated at a relatively constant wall temperature ratio.
Download or read book A Discussion of Methods for Reducing Aerodynamic Heating in Supersonic Flight written by A. J. Eggers (Jr.) and published by . This book was released on 1955 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
