Effects Of Leading Edge Sweep Angle And Design Lift Coefficient On Performance Of A Modified Arrow Wing At A Design Mach Number Of 2 6
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Effects Of Leading Edge Sweep Angle And Design Lift Coefficient On Performance Of A Modified Arrow Wing At A Design Mach Number Of 2 6
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Author : Robert J. Mack
language : en
Publisher:
Release Date : 1974
Effects Of Leading Edge Sweep Angle And Design Lift Coefficient On Performance Of A Modified Arrow Wing At A Design Mach Number Of 2 6 written by Robert J. Mack and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Aerodynamics, Supersonic categories.
Wing models were tested in the high-speed section of the Langley Unitary Plan wind tunnel to study the effects of the leading-edge sweep angle and the design lift coefficient on aerodynamic performance and efficiency. The models had leading-edge sweep angles of 69.44 deg, 72.65 deg, and 75.96 deg which correspond to values of the design Mach-number-sweep-angle parameter (beta cotangent A) sub DES of 0.6, 0.75, and 0.9, respectively. For each sweep angle, camber surfaces having design lift coefficients of 0,0.08, and 0.12 at a design Mach number of 2.6 were generated. The wind-tunnel tests were conducted at Mach numbers of 2.3, 2.6, and 2.96 with a stagnation temperature of 338.7 K (150 F) and a Reynolds number per meter of 9.843 times 10 to the 6th power. The results of the tests showed that only a moderate sweeping of the wing leading edge aft of the Mach line along with a small-to-moderate amount of camber and twist was needed to significantly improve the zero-lift (flat camber surface) wing performance and efficiency.
Nasa Technical Paper
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Author :
language : en
Publisher:
Release Date : 1992
Nasa Technical Paper 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.
Nasa Technical Note
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Author :
language : en
Publisher:
Release Date : 1974
Nasa Technical Note written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with categories.
Scientific And Technical Aerospace Reports
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Author :
language : en
Publisher:
Release Date : 1980
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 1980 with Aeronautics categories.
Monthly Catalog Of United States Government Publications Cumulative Index
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Author : United States. Superintendent of Documents
language : en
Publisher:
Release Date : 1976
Monthly Catalog Of United States Government Publications Cumulative Index written by United States. Superintendent of Documents and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1976 with United States categories.
Aerodynamic Characteristics Of Wings Designed With A Combined Theory Method To Cruise At A Mach Number Of 4 5
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Author : Robert J. Mack
language : en
Publisher:
Release Date : 1988
Aerodynamic Characteristics Of Wings Designed With A Combined Theory Method To Cruise At A Mach Number Of 4 5 written by Robert J. Mack and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1988 with Aerodynamics, Hypersonic categories.
Monthly Catalog Of United States Government Publications
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Author :
language : en
Publisher:
Release Date : 1971
Monthly Catalog Of United States Government Publications written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Government publications categories.
Government Reports Annual Index
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Author :
language : en
Publisher:
Release Date : 1975
Government Reports Annual 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 1975 with Government reports announcements & index categories.
Survey And Analysis Of Research On Supersonic Drag Due To Lift Minimization With Recommendations For Wing Design
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Author : Harry W. Carlson
language : en
Publisher:
Release Date : 1992
Survey And Analysis Of Research On Supersonic Drag Due To Lift Minimization With Recommendations For Wing Design written by Harry W. Carlson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with Aerodynamics, Supersonic categories.
A Reynolds Number Study Of Wing Leading Edge Effects On A Supersonic Transport Model At Mach 0 3
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Author : M. Susan Williams
language : en
Publisher:
Release Date : 1999
A Reynolds Number Study Of Wing Leading Edge Effects On A Supersonic Transport Model At Mach 0 3 written by M. Susan Williams and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1999 with categories.
A representative supersonic transport design was tested in the National Transonic Facility (NTF) in its original configuration with small-radius leading-edge flaps and also with modified large-radius inboard leading-edge flaps. Aerodynamic data were obtained over a range of Reynolds numbers at a Mach number of 0.3 and angles of attack up to 16 deg. Increasing the radius of the inboard leading-edge flap delayed nose-up pitching moment to a higher lift coefficient. Deflecting the large-radius leading-edge flap produced an overall decrease in lift coefficient and delayed nose-up pitching moment to even higher angles of attack as compared with the undeflected large- radius leading-edge flap. At angles of attack corresponding to the maximum untrimmed lift-to-drag ratio, lift and drag coefficients decreased while lift-to-drag ratio increased with increasing Reynolds number. At an angle of attack of 13.5 deg., the pitching-moment coefficient was nearly constant with increasing Reynolds number for both the small-radius leading-edge flap and the deflected large-radius leading-edge flap. However, the pitching moment coefficient increased with increasing Reynolds number for the undeflected large-radius leading-edge flap above a chord Reynolds number of about 35 x 10 (exp 6).