Transonic Aerodynamic Loading Characteristics Of A Wing Body Tail Combination Having 52 5 Sweptback Wing Of Aspect Ratio 3 With Conical Wing Camber And Body Indentation For A Design Mach Number Square Root Of 2
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Transonic Aerodynamic Loading Characteristics Of A Wing Body Tail Combination Having 52 5 Sweptback Wing Of Aspect Ratio 3 With Conical Wing Camber And Body Indentation For A Design Mach Number Square Root Of 2
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Author : Marlowe D. Cassetti
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Loading Characteristics Of A Wing Body Tail Combination Having 52 5 Sweptback Wing Of Aspect Ratio 3 With Conical Wing Camber And Body Indentation For A Design Mach Number Square Root Of 2 written by Marlowe D. Cassetti and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Transonic wind tunnels categories.
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Transonic Aerodynamic Loading Characteristics Of A Wing Body Tail Combination Having A 52 5 Degree Sweptback Wing Of Aspect Ratio 3 With Conical Wing Camber And Body Indentation For A Design Mach Number Of The Square Root Of 2
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Author : MARLOWE D. CASSETTI
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Loading Characteristics Of A Wing Body Tail Combination Having A 52 5 Degree Sweptback Wing Of Aspect Ratio 3 With Conical Wing Camber And Body Indentation For A Design Mach Number Of The Square Root Of 2 written by MARLOWE D. CASSETTI 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 inves iga io as been made of the effects of conical wing camber and body indentation ccordi g to t e supersonic area rule on the aerodynamic wing loading characteristics of a wingbody-tail configuration at transonic speeds. The wing aspect ratio was 3, aper ratio was 0.1, and quarter-chord-line sweepback was 52.5 deg with 3-perc t- ick airfoil sec ions. The tests were conducted in the Langley 16-foot transonic unnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0 to 14 deg with Rey olds numbers based on mean aerodyna ic chord varying from 7 x 10 to the 6th power to 8 x 10 to the 6th power. Conical camber delayed wing-tip stall and r duced s verity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced the transonic chordwise centerof-pressure travel from about 8 percent to 5 percent of the mean aerodyn mic chord. (Author).
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 5 Deg Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of The Square Root Of 2
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Author : William B. Igoe
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 5 Deg Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of The Square Root Of 2 written by William B. Igoe 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.
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 20 Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 2
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Author : William B. Igoe
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 20 Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 2 written by William B. Igoe 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.
Transonic Aerodynamic Characteristics Of A Wingbody Combination Having A 52 5 Degree Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 1 1416
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Author : WILLIAM B. IGOE
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Characteristics Of A Wingbody Combination Having A 52 5 Degree Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 1 1416 written by WILLIAM B. IGOE 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 was made of the effects of conical wing camber and supersonic body indentation on the aerodynamic characteristics of a wing-body configuration at transonic speeds. Wing aspect ratio was 3.0, taper ratio was 0.1, and quarterchord line sweepback was 52.5 with airfoil sections of 0.03 thickness ratio. The tests were conducted in the Langley 16-foot transonic tunnel at various Mach numbers from 0.80 to 1.05 at angles of attack from -4 to 14. The camberedwing configuration achieved higher lift-drag ratios than a similar plane-wing configuration. The camber also reduced the effects of wing-tip flow separation on the aerodynamic characteristics. In general, no stability or trim changes below wing-tip flow separation resulted from the use of camber. The use of supersonic body indentation improved the lift-drag ratios at Mach numbers from 0.96 to 1.05. (Author).
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 2 Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 2
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Author : William B. Igoe
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 2 Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 2 written by William B. Igoe 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.
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 5 Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 2
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Author : William B. Igoe
language : en
Publisher:
Release Date : 1961
Transonic Aerodynamic Characteristics Of A Wing Body Combination Having A 52 5 Sweptback Wing Of Aspect Ratio 3 With Conical Camber And Designed For A Mach Number Of 2 written by William B. Igoe 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, aircraft 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 : 1956
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 1956 with Aerodynamic load 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 has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
The Effects Of Wing Incidence On The Aerodynamic Loading Characteristics Of A Sweptback Wing Body Combination At Transonic Speeds
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Author : Harold L. Robinson
language : en
Publisher:
Release Date : 1954
The Effects Of Wing Incidence On The Aerodynamic Loading Characteristics Of A Sweptback Wing Body Combination At Transonic Speeds written by Harold L. Robinson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Aerodynamic load categories.
An Experimental Transonic Investigation Of A 45 Sweptback Wing Body Combination With Several Types Of Body Indentation With Theoretical Comparisons Included
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Author : Melvin M. Carmel
language : en
Publisher:
Release Date : 1954
An Experimental Transonic Investigation Of A 45 Sweptback Wing Body Combination With Several Types Of Body Indentation With Theoretical Comparisons Included written by Melvin M. Carmel 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.