Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone Cylinder At Hypersonic Free Flight Mach Numbers Up To 20 4
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Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone Cylinder At Hypersonic Free Flight Mach Numbers Up To 20 4
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Author :
language : en
Publisher:
Release Date : 1964
Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone Cylinder At Hypersonic Free Flight Mach Numbers Up To 20 4 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with categories.
Scientific And Technical Aerospace Reports
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Author :
language : en
Publisher:
Release Date : 1966
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Aeronautics categories.
International Aerospace Abstracts
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Author :
language : en
Publisher:
Release Date : 1993
International Aerospace Abstracts written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with Aeronautics categories.
Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone During Free Flight At Mach Numbers Up To 20 8
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Author :
language : en
Publisher:
Release Date : 1963
Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone During Free Flight At Mach Numbers Up To 20 8 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with categories.
Free Flight Hypersonic Heat Transfer And Boundary Layer Transition Studies
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Author : James E. Brunk
language : en
Publisher:
Release Date : 1961
Free Flight Hypersonic Heat Transfer And Boundary Layer Transition Studies written by James E. Brunk and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Aerodynamic heating categories.
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.
Heat Transfer And Pressure Distributions On Spherically Blunted 25 Half Angle Cone At Mach 8 And Angles Of Attack Up To 90
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Author : Dennis M. Bushnell
language : en
Publisher:
Release Date : 1968
Heat Transfer And Pressure Distributions On Spherically Blunted 25 Half Angle Cone At Mach 8 And Angles Of Attack Up To 90 written by Dennis M. Bushnell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with Aerodynamics categories.
A Study Of Laminar Heat Transfer To Spherically Blunted Cones And Hemisphere Cylinders At Hypersonic Conditions
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Author : B. J. Griffith
language : en
Publisher:
Release Date : 1963
A Study Of Laminar Heat Transfer To Spherically Blunted Cones And Hemisphere Cylinders At Hypersonic Conditions written by B. J. Griffith and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with Heat categories.
Free Flight Measurements Of Aerodynamic Heat Transfer To Mach Number 3 9 And Of Drag To Mach Number 6 9 Of A Fin Stabilized Cone Cylinder Configuration
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Author : Charles B. Rumsey
language : en
Publisher:
Release Date : 1955
Free Flight Measurements Of Aerodynamic Heat Transfer To Mach Number 3 9 And Of Drag To Mach Number 6 9 Of A Fin Stabilized Cone Cylinder Configuration written by Charles B. Rumsey and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Aerodynamic heating categories.
Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
Measurements Of Aerodynamic Heat Transfer On A 15 Deg Cone Cylinder Flare Configuration In Free Flight At Mach Numbers Up To 4 7
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Author : CHARLES B. RUMSEY
language : en
Publisher:
Release Date : 1961
Measurements Of Aerodynamic Heat Transfer On A 15 Deg Cone Cylinder Flare Configuration In Free Flight At Mach Numbers Up To 4 7 written by CHARLES B. RUMSEY and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with categories.
Measurements of aerodynamic heat transfer were made at a number of stations along a cone-cylinder-flare model having a 15 degrees total-angle conical nose and a 10 degrees half-angle flare skirt. The maximum Mach number was 4.7, and local Reynolds numbers based on body length to a measurement station varied from 2 x 10 to the 6th power to 138 x 10 to the 6th power. Local Stanton numbers measured on the nose cone and flare showed fair agreement with laminar and turbulent theories, while the measurements on the cylinder were generally somewhat lower than theory. Experimental recovery factors, determined twice during the test, were unaccountably lower than theoretical values. Local transition Reynolds numbers, based on length from the nose tip, varied from 3 x 10 to the 6th power to 18 x 10 to the 6th power and were much lower than values previously obtained on the smoother nose of a similar model. At an angle of attack of about 9 degrees, the heat transfer on the flare increased to more than twie the theoretical turbulent value for zero angle of attack. (Author).
Convective Heat Transfer Rates On A Blunted 110 Cone With Hemispherical Afterbody At Hypersonic Speeds
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Author : David A. Stewart
language : en
Publisher:
Release Date : 1971
Convective Heat Transfer Rates On A Blunted 110 Cone With Hemispherical Afterbody At Hypersonic Speeds written by David A. Stewart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Cone categories.