Hypersonic Laminar Heat Transfer And Boundary Layer Transition On Sharp And Blunted Cones
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Author | : N. B. Wood |
Publisher | : |
Total Pages | : 41 |
Release | : 1968 |
Genre | : |
ISBN | : |
Download Hypersonic Laminar Heat Transfer and Boundary Layer Transition on Sharp and Blunted Cones 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 | : David E. Boylan |
Publisher | : |
Total Pages | : 68 |
Release | : 1973 |
Genre | : Aerodynamic heating |
ISBN | : |
Download Laminar Heat Transfer on Sharp and Blunt Ten-degree Cones in Conical and Parallel Low-density Flow Book in PDF, Epub and Kindle
The report presents heat-transfer-rate measurements on sharp and blunt 10-deg half-angle cones at angles of attack between -9 and +10 deg in a low-density, hypersonic wind tunnel. Circumferential and longitudinal distributions are presented for cold wall conditions for a range at Mach and Reynolds numbers. The effect of source-like flows was studied by utilizing both conical and contoured expansion nozzles with the same free-stream similarity parameters and model wall temperatures. Comparisons are made with previously published experimental and theoretical results. (Author).
Author | : Raul Jorge Conti |
Publisher | : |
Total Pages | : 38 |
Release | : 1961 |
Genre | : Heat |
ISBN | : |
Download Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° Book in PDF, Epub and Kindle
Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Author | : Michael C. Fischer |
Publisher | : |
Total Pages | : 76 |
Release | : 1970 |
Genre | : Aerodynamics |
ISBN | : |
Download An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 Book in PDF, Epub and Kindle
Boundary layer transition on nose cones at hypersonic speeds.
Author | : Kenneth F. Stetson |
Publisher | : |
Total Pages | : 92 |
Release | : 1980 |
Genre | : Angle of attack (Aerodynamics) |
ISBN | : |
Download Hypersonic Boundary Layer Transition Experiments Book in PDF, Epub and Kindle
Author | : Albert H. Boudreau |
Publisher | : |
Total Pages | : 50 |
Release | : 1978 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download Artificially Induced Boundary-layer Transition on Blunt-slender Cones Using Distributed Roughness and Spherical-type Tripping Devices at Hypersonic Speeds Book in PDF, Epub and Kindle
Research directed toward establishing criteria for distributed roughness-type boundary-layer trips on blunt-slender cones has been conducted in the AEDC/VKF at Mach numbers from 8 to 13. Results indicate that distributed roughness trips are superior to spherical-type trips in that equally effective distributed roughness trips are one-fifth as high and produce substantially smaller flow-field disturbances. Criteria are defined for optimum utilization of distributed roughness trips.
Author | : Michael E. Tauber |
Publisher | : |
Total Pages | : 44 |
Release | : 1989 |
Genre | : Aerodynamic heating |
ISBN | : |
Download A Review of High-speed, Convective, Heat-transfer Computation Methods Book in PDF, Epub and Kindle
Author | : James E. Brunk |
Publisher | : |
Total Pages | : 0 |
Release | : 1960 |
Genre | : |
ISBN | : |
Download Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies Book in PDF, Epub and Kindle
Author | : Albert H. Boudreau |
Publisher | : |
Total Pages | : 18 |
Release | : 1979 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download A Correlation of Artifically Induced Boundary-layer Transition Data from Blunt Slender Cones at Hypersonic Speeds Book in PDF, Epub and Kindle