Effect Of Mach Number On Boundary Layer Transition In The Presence Of Pressure Rise And Surface Roughness On An Ogive Cylinder Body With Cold Wall Conditions
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Author | : Robert J. Carros |
Publisher | : |
Total Pages | : 30 |
Release | : 1956 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download Effect of Mach Number on Boundary-layer Transition in the Presence of Pressure Rise and Surface Roughness on an Ogive-cylinder Body with Cold Wall Conditions Book in PDF, Epub and Kindle
The effect of Mach number variation from 1.8 to 7.4 on boundary-layer transition was investigated on a slender fin-stabilized ogive-cylinder body in free flight at a constant length Reynolds number of 13.8 million. The wall to free-stream temperature ratio was constant at a value of 1.0 below Mach number 4.5 and at a value of 1.8 above Mach number 4.5. Results of the test showed that increasing Mach number had a very favorable effect of increasing the extent of the laminar boundary layer for a given surface roughness. The transition data, when plotted as a function of a factor indicative of heat transfer, showed that heat transfer was possibly responsible for a good deal of the increase in transition Reynolds number with Mach number.
Author | : |
Publisher | : |
Total Pages | : 1188 |
Release | : 1961 |
Genre | : Aeronautics |
ISBN | : |
Download NASA Technical Note Book in PDF, Epub and Kindle
Author | : Alvin Seiff |
Publisher | : |
Total Pages | : 74 |
Release | : 1961 |
Genre | : Aerodynamics |
ISBN | : |
Download Experimental Investigation of a Hypersonic Glider Configuration at a Mach Number of 6 and at Full-scale Reynolds Numbers Book in PDF, Epub and Kindle
Author | : James E. Brunk |
Publisher | : |
Total Pages | : 168 |
Release | : 1961 |
Genre | : Aerodynamic heating |
ISBN | : |
Download Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies Book in PDF, Epub and Kindle
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.
Author | : Mark Vladimir Morkovin (|d) |
Publisher | : |
Total Pages | : 152 |
Release | : 1969 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download Critical Evaluation of Transition from Laminar to Turbulent Shear Layers with Emphasis on Hypersonically Traveling Bodies Book in PDF, Epub and Kindle
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 678 |
Release | : 1958 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download NACA Conference on High-Speed Aerodynamics Book in PDF, Epub and Kindle
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 382 |
Release | : 1959 |
Genre | : Aeronautics |
ISBN | : |
Download Index of NACA Technical Publications Book in PDF, Epub and Kindle
Author | : United States. National Aeronautics and Space Administration |
Publisher | : |
Total Pages | : 506 |
Release | : 1959 |
Genre | : Aeronautics |
ISBN | : |
Download NASA Memorandum Book in PDF, Epub and Kindle
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 716 |
Release | : 1956 |
Genre | : Aeronautics |
ISBN | : |
Download Research Abstracts and Reclassification Notice Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 74 |
Release | : 1958 |
Genre | : Aeronautics |
ISBN | : |
Download NASA Memorandum Book in PDF, Epub and Kindle