Pressure Distributions On Blunt Delta Wings At A Mach Number Of 2 91 And Angles Of Attack Up To 90 Deg

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Pressure Distributions On Blunt Delta Wings At A Mach Number Of 2 91 And Angles Of Attack Up To 90 Deg

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Author :
language : en
Publisher:
Release Date : 1962

Pressure Distributions On Blunt Delta Wings At A Mach Number Of 2 91 And Angles Of Attack Up To 90 Deg written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1962 with categories.

Scientific And Technical Aerospace Reports

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Author :
language : en
Publisher:
Release Date : 1994

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 1994 with Aeronautics categories.

Aeronautical Engineering

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Author :
language : en
Publisher:
Release Date : 1991

Aeronautical Engineering written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aeronautics 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°.

Nasa Sp

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Author :
language : en
Publisher:
Release Date : 1992

Nasa Sp written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with Aeronautics categories.

Government Reports Announcements Index

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Author :
language : en
Publisher:
Release Date : 1992

Government Reports Announcements Index written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with Science categories.

Aeronautical Engineering A Cumulative Index To A Continuing Bibliography Supplement 274

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Author :
language : en
Publisher:
Release Date : 1992

Aeronautical Engineering A Cumulative Index To A Continuing Bibliography Supplement 274 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with categories.

The Aeronautical Journal

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Author :
language : en
Publisher:
Release Date : 1969

The Aeronautical Journal written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1969 with Aeronautics categories.

International Aerospace Abstracts

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Author :
language : en
Publisher:
Release Date : 1996

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 1996 with Aeronautics categories.

Pressure Distributions On Blunt Delta Wings At Angles Of Attack Up To 90 Degrees And Mach Number Of 6 85

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Author : Peter T. Bernot
language : en
Publisher:
Release Date : 1963

Pressure Distributions On Blunt Delta Wings At Angles Of Attack Up To 90 Degrees And Mach Number Of 6 85 written by Peter T. Bernot and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with Mach number categories.