Heat Transfer Measurements At A Mach Number Of 4 95 On Two 60 Degree Sweot Delta Wings With Blunt Leading Edges And Dihedral Angles Of 0 Degrees And 46 Degrees
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Heat Transfer Measurements At A Mach Number Of 4 95 On Two 60 Degree Sweot Delta Wings With Blunt Leading Edges And Dihedral Angles Of 0 Degrees And 46 Degrees
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Author : P. Calvin Stainback
language : en
Publisher:
Release Date : 1961
Heat Transfer Measurements At A Mach Number Of 4 95 On Two 60 Degree Sweot Delta Wings With Blunt Leading Edges And Dihedral Angles Of 0 Degrees And 46 Degrees written by P. Calvin Stainback 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.
Heat Transfer Distribution On 700 Swept Slab Delta Wings At A Mach Number Of 9 86 And Angles Of Attack Up To 900
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Author : Philip E. Everhart
language : en
Publisher:
Release Date : 1964
Heat Transfer Distribution On 700 Swept Slab Delta Wings At A Mach Number Of 9 86 And Angles Of Attack Up To 900 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 1964 with Aerodynamics, Hypersonic categories.
Heat-transfer distributions were obtained on 700 swept slab delta wings with sharp and blunt noses and cylindrical leading edges. The free-stream Reynolds number based on model thickness was 9 x 10(4). Lees' theory for the heat-transfer distribution is shown to be in good agreement with the data obtained on the nose and leading edge. The point of peak heating on the leading edge is in close agreement with the Newtonian stagnation point at all angles of attack. At angles of attack from 40° to 60° cross-flow theory was in excellent agreement with experimental center-line data; however, at other model attitudes the theory differed significantly from experiment. Nose blunting resulted in reduced heating rates over the aft center-line section of the wing at angles of attack less than about 40°.
An Experimental Study Of The Pressure And Heat Transfer Distribution On A 70 Sweep Slab Delta Wing In Hypersonic Flow
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Author : Mitchel H. Bertram
language : en
Publisher:
Release Date : 1963
An Experimental Study Of The Pressure And Heat Transfer Distribution On A 70 Sweep Slab Delta Wing In Hypersonic Flow written by Mitchel H. Bertram and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with Aerodynamics, Hypersonic categories.
Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Heat Transfer And Pressure Distributions On 60 And 70 Swept Delta Wings Having Turbulent Boundary Layers
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Author : William M. Murray (Jr.)
language : en
Publisher:
Release Date : 1966
Heat Transfer And Pressure Distributions On 60 And 70 Swept Delta Wings Having Turbulent Boundary Layers written by William M. Murray (Jr.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Airplanes categories.
Heat Transfer To 0 Degree And 75 Degree Swept Blunt Leading Edges In Free Flight At Mach Numbers From 1 90 To 3 07
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Author : Robert L. O'Neal
language : en
Publisher:
Release Date : 1962
Heat Transfer To 0 Degree And 75 Degree Swept Blunt Leading Edges In Free Flight At Mach Numbers From 1 90 To 3 07 written by Robert L. O'Neal and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with Heat categories.
A Visual Technique For Determining Qualitative Aerodynamic Heating Rates On Complex Configurations
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Author : P. Calvin Stainback
language : en
Publisher:
Release Date : 1960
A Visual Technique For Determining Qualitative Aerodynamic Heating Rates On Complex Configurations written by P. Calvin Stainback and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aerothermodynamics categories.
"An experimental investigation was conducted at a test-section Mach number of 4.95 and a stagnation temperature of 400 degrees F to evaluate a visual technique for obtaining qualitative aerodynamic heat-transfer data on complex configurations. This technique utilized a temperature-sensitive paint which exhibited the characteristic that a pronounced color change occurred at a known temperature. The visual results obtained with the temperature-sensitive paint indicated that this technique was satisfactory for determining qualitative heat-transfer rates on various bodies, some of which exhibited complex flow patterns. The results obtained have been found useful to guide the instrumentation of quantitative heat-transfer models, to supplement quantitative heat-transfer measurements, and to make preliminary heat-transfer studies for new configurations."p.[1].
Pressures And Heat Transfer On A 75 Swept Delta Wing With Trailing Edge Flap At Mach 6 And Angles Of Attack To 90
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Author : J. Wayne Keyes
language : en
Publisher:
Release Date : 1969
Pressures And Heat Transfer On A 75 Swept Delta Wing With Trailing Edge Flap At Mach 6 And Angles Of Attack To 90 written by J. Wayne Keyes and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with Aerodynamic heating categories.
Pressure and heat transfer on swept delta wing with trailing-edge flap.
Heat Transfer To A Delta Wing Half Cone Combination At Mach Numbers Of 7 And 10
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Author : James C. Dunavant
language : en
Publisher:
Release Date : 1964
Heat Transfer To A Delta Wing Half Cone Combination At Mach Numbers Of 7 And 10 written by James C. Dunavant and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Aerodynamic heating categories.
Analysis Of Hypersonic Pressure And Heat Transfer Tests On Delta Wings With Laminar And Turbulent Boundary Layers Final Report
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Author :
language : en
Publisher:
Release Date : 1966
Analysis Of Hypersonic Pressure And Heat Transfer Tests On Delta Wings With Laminar And Turbulent Boundary Layers Final Report 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 categories.
Heat Transfer And Pressure Measurements On Delta Wings At Mach Numbers Of 3 51 And 4 65 And Angles Of Attack From 45 To 45
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Author : Robert L. Stallings
language : en
Publisher:
Release Date : 1964
Heat Transfer And Pressure Measurements On Delta Wings At Mach Numbers Of 3 51 And 4 65 And Angles Of Attack From 45 To 45 written by Robert L. Stallings and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Airplanes categories.