Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 Degrees 70 Degrees And 90 Degrees
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Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 Degrees 70 Degrees And 90 Degrees
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Author : James L. Hunt
language : en
Publisher:
Release Date : 1969
Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 Degrees 70 Degrees And 90 Degrees written by James L. Hunt and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with categories.
Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 70 And 90
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Author : James Larry Hunt
language : en
Publisher:
Release Date : 1969
Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 70 And 90 written by James Larry Hunt and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with Angle of attack (Aerodynamics) categories.
Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 70 And 90
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Author : James L. Hunt
language : en
Publisher:
Release Date : 1969
Heat Transfer To The Windward Side Of A Fineness Ratio 2 9 Cylinder With Nearly Spherical Ends At A Mach Number Of 6 And Angles Of Attack Of 50 70 And 90 written by James L. Hunt and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with categories.
Heat Transfer Measurements On A Low Fineness Ratio Cylinder At A Mach Number Of 10 4 And Angles Of Attack From 0 To 90
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Author : Philip E. Everhart
language : en
Publisher:
Release Date : 1967
Heat Transfer Measurements On A Low Fineness Ratio Cylinder At A Mach Number Of 10 4 And Angles Of Attack From 0 To 90 written by Philip E. Everhart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Airplanes categories.
Heat Transfer Measurements On A Low Fineness Ratio Cylinder At A Mach Number Of 10 4 And Angles Of Attack From 0 To 90
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Author : Philip E. Everhart
language : en
Publisher:
Release Date : 1967
Heat Transfer Measurements On A Low Fineness Ratio Cylinder At A Mach Number Of 10 4 And Angles Of Attack From 0 To 90 written by Philip E. Everhart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with Airplanes categories.
Heat Transfer And Pressure Measurements On A Flat Face Cylinder At A Mach Number Range Of 2 49 To 4 44
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Author : Paige B. Burbank
language : en
Publisher:
Release Date : 1959
Heat Transfer And Pressure Measurements On A Flat Face Cylinder At A Mach Number Range Of 2 49 To 4 44 written by Paige B. Burbank and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Aerodynamic heating categories.
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).
Measurements Of Aerodynamic Heat Transfer On A 15 Degree Cone Cylinder Flare Configuration In Free Flight At Mach Numbers Up To 4 7
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Author : Charles R. Rumsey
language : en
Publisher:
Release Date : 1961
Measurements Of Aerodynamic Heat Transfer On A 15 Degree Cone Cylinder Flare Configuration In Free Flight At Mach Numbers Up To 4 7 written by Charles R. 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 Fluid mechanics categories.
Local Heat Transfer And Recovery Temperatures On A Yawed Cylinder At A Mach Number Of 4 15 And High Reynolds Numbers
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Author : Ivan E. Beckwith
language : en
Publisher:
Release Date : 1961
Local Heat Transfer And Recovery Temperatures On A Yawed Cylinder At A Mach Number Of 4 15 And High Reynolds Numbers written by Ivan E. Beckwith and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Hypersonic planes categories.
Local heat transfer, equilibrium temperatures, and pressure have been measured on a circular cylinder for yaw angles from 0° to 60° and Reynolds numbers from 1X106 to 4X106. Increasing the yaw angle from 0° to 40° generally caused large increases in local heat-transfer coefficients followed by a decrease as the yaw angle was increased to 60°. The level of heating rates and the type if chordwise distribution indicated that a flow mechanism different from the conventional transitional boundary layer may exist for the intermediate yaw angles.
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.