Investigation At Mach Numbers From 0 80 To 1 43 Of Pressure And Load Distributions Over A Thin 45 Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies

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Investigation At Mach Numbers From 0 80 To 1 43 Of Pressure And Load Distributions Over A Thin 45 Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies

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Author : Thomas L. Fischetti
language : en
Publisher:
Release Date : 1957

Investigation At Mach Numbers From 0 80 To 1 43 Of Pressure And Load Distributions Over A Thin 45 Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies written by Thomas L. Fischetti and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerodynamic load categories.

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.

Investigation At Mach Numbers From 0 80 To 1 43 Of Pressure And Load Distributions Over A Thin 45 Degree Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies

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Author : Thomas L. Fischetti
language : en
Publisher:
Release Date : 1957

Investigation At Mach Numbers From 0 80 To 1 43 Of Pressure And Load Distributions Over A Thin 45 Degree Sweptback Highly Tapered Wing In Combination With Basic And Indented Bodies written by Thomas L. Fischetti and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerodynamic load categories.

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.

Basic Pressure Measurements At A Mach Number Of 1 43 On A Thing 45 Degree Sweptback Highly Tapered Wing With Systematic Spanwise Twist Variations

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Author : John P. Jr Mugler
language : en
Publisher:
Release Date : 1960

Basic Pressure Measurements At A Mach Number Of 1 43 On A Thing 45 Degree Sweptback Highly Tapered Wing With Systematic Spanwise Twist Variations written by John P. Jr Mugler and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Wall pressure (Aerodynamics) categories.

Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic, and cubic twist variations along the span. All the twisted wings had 0 degrees twist at the 10-percent-semispan station and 6 degrees twist at he tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4 degrees to 20 degrees. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 X 10(6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 X 10(6) during tests at a stagnation pressure of 0.5 atmosphere.

Basic Pressure Measurements At A Mach Number Of 1 43 On A Thin 45 Deg Sweptback Highly Tapered Wing With Systematic Spanwise Twist Variations

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Author :
language : en
Publisher:
Release Date : 1960

Basic Pressure Measurements At A Mach Number Of 1 43 On A Thin 45 Deg Sweptback Highly Tapered Wing With Systematic Spanwise Twist Variations written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.

Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and wings with linear, quadratic and cubic twist variations along the span. All the twisted wings had 0deg twist at the 10-percent-semispan station and 6deg twist at the tip. The tests were made at a Mach number of 1.43 and covered an angle-of-attack range from -4deg to 20deg. The average Reynolds number based on the wing mean aerodynamic chord was 2.9 x 10(exp 6) during tests at a stagnation pressure of 1.0 atmosphere and 1.5 x 10(exp 6) during tests at a stagnation pressure of 0.5 atmosphere.

Basic Pressure Measurements At A Mach Number Of 1 43 On A Thin 45 Sweptback Highly Tapered Wing With Systematic Spanwise Twist Variations

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Author : John P. Mugler
language : en
Publisher:
Release Date : 1960

Basic Pressure Measurements At A Mach Number Of 1 43 On A Thin 45 Sweptback Highly Tapered Wing With Systematic Spanwise Twist Variations written by John P. Mugler and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.

A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Degree Sweptback Wing Body Combination Designed For High Performance

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Author : Donald L. Loving
language : en
Publisher:
Release Date : 1961

A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Degree Sweptback Wing Body Combination Designed For High Performance written by Donald L. Loving and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Aerodynamics categories.

Investigation At Transonic Speeds Of The Loading Over A 45 Degree Sweptback Wing Having An Aspect Ratio Of 3 A Taper Ratio Of 0 2 And Naca 65a004 Airfoil Sections

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Author : JACK F. RUNCKEL
language : en
Publisher:
Release Date : 1961

Investigation At Transonic Speeds Of The Loading Over A 45 Degree Sweptback Wing Having An Aspect Ratio Of 3 A Taper Ratio Of 0 2 And Naca 65a004 Airfoil Sections written by JACK F. RUNCKEL 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.

An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).

A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Degrees Sweptback Wing Body Combination Designed For High Performance

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Author : Donald L. Loving
language : en
Publisher:
Release Date : 1956

A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Degrees Sweptback Wing Body Combination Designed For High Performance written by Donald L. Loving and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with categories.

A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Sweptback Wing Body Combination Designed For High Performance

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Author : Donald L. Loving
language : en
Publisher:
Release Date : 1961

A Transonic Investigation Of Changing Indentation Design Mach Number On The Aerodynamic Characteristics Of A 45 Sweptback Wing Body Combination Designed For High Performance written by Donald L. Loving 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.

A Flight Investigation Of The Transonic Area Rule For A 52 5 Sweptback Wind Body Configuration At Mach Numbers Between 0 8 And 1 6

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Author : Sherwood Hoffman
language : en
Publisher:
Release Date : 1954

A Flight Investigation Of The Transonic Area Rule For A 52 5 Sweptback Wind Body Configuration At Mach Numbers Between 0 8 And 1 6 written by Sherwood Hoffman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Aerodynamics, Transonic categories.