Pressure Distributions On A Flat Plate Delta Wing Swept 65 Deg At A Mach Number Of 5 97 At Angles Of Attack From 65 Deg To 115 Deg And Angles Of Roll From 0 Deg To 25 Deg At A 90 Deg Angle Of Attack
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Government Wide Index To Federal Research Development Reports
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Author :
language : en
Publisher:
Release Date : 1966-11
Government Wide Index To Federal Research Development 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 1966-11 with Government publications categories.
Pressure Distributions On A Flat Plate Delta Wing Swept 65 Deg At A Mach Number Of 5 97 At Angles Of Attack From 65 Deg To 115 Deg And Angles Of Roll From 0 Deg To 25 Deg At A 90 Deg Angle Of Attack
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Author :
language : en
Publisher:
Release Date : 1962
Pressure Distributions On A Flat Plate Delta Wing Swept 65 Deg At A Mach Number Of 5 97 At Angles Of Attack From 65 Deg To 115 Deg And Angles Of Roll From 0 Deg To 25 Deg At A 90 Deg Angle Of Attack 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.
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.
Effects Of Rounding Corners And Leading Edges On The Windward Surface Pressures Of A Delta Wing Swept 650 At A Mach Number Of 5 96 At Angles Of Attack From 650 To 1150 And Angles Of Roll From O0 To 250 At 900 Angle Of Attack
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Author : Theodore J. Goldberg
language : en
Publisher:
Release Date : 1963
Effects Of Rounding Corners And Leading Edges On The Windward Surface Pressures Of A Delta Wing Swept 650 At A Mach Number Of 5 96 At Angles Of Attack From 650 To 1150 And Angles Of Roll From O0 To 250 At 900 Angle Of Attack written by Theodore J. Goldberg 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 categories.
Heat Transfer And Pressure Distributions Of A 60 Deg Delta Wing With Dihedral At A Mach Number Of 6 And Angles Of Attack From 0 Deg To 52 Deg
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Author :
language : en
Publisher:
Release Date : 1961
Heat Transfer And Pressure Distributions Of A 60 Deg Delta Wing With Dihedral At A Mach Number Of 6 And Angles Of Attack From 0 Deg To 52 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 1961 with categories.
A Method For Predicting The Normal Force Characteristics Of Delta Wings At Angles Of Attack From 0 Deg To 90 Deg
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Author :
language : en
Publisher:
Release Date : 1963
A Method For Predicting The Normal Force Characteristics Of Delta Wings At Angles Of Attack From 0 Deg 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 1963 with categories.
Experimental Study And Analysis Of Loading And Pressure Distributions On Delta Wings Due To Thickness And To Angle Of Attack At Supersonic Speeds
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Author : William B. Boatright
language : en
Publisher:
Release Date : 1956
Experimental Study And Analysis Of Loading And Pressure Distributions On Delta Wings Due To Thickness And To Angle Of Attack At Supersonic Speeds written by William B. Boatright 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.
The aerodynamic loading on delta wings at supersonic speed was studied principally to determine the coupling and nonlinear interference effects between the pressures due to angle of attack and due to thickness. Pressure distributions on four delta wings having leading-edge sweep angles of 53, 60, and 66.6 degrees were measured at Mach numbers of 1.62, 1.93, and 2.41. Three wings had NACA 65A003 sections. The other wing had a flat upper surface and a leading-edge sweep angle of 53 degrees. At Mach numbers of 1.94 and 2.41, some of the results for this wing simulate a wing of zero thickness; the pressure distributions are compared with the pressure distributions of an NACA 65A003 section wing of the same plan form. For this comparison the pressure distributions at zero angle of attack deducted. Appreciable nonlinear interference effects are shown to exist such that the pressure distributions caused by angle of attack are not additive at test angles of attack greater than 5 degrees. These effects are shown to exist for all the NACA 65A003 section wings at all test Mach numbers, and in each case the experimental results are compared with theory.
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.
Experimental Surface Pressure Data Obtained On 65 Delta Wing Across Reynolds Number And Mach Number Ranges
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Author : Julio Chu
language : en
Publisher:
Release Date : 1996
Experimental Surface Pressure Data Obtained On 65 Delta Wing Across Reynolds Number And Mach Number Ranges written by Julio Chu and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with Angle of attack categories.
Effect Of Sideslip On The Flow Over A 65 Deg Delta Wing
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Author : Nicolaas Verhaagen
language : en
Publisher:
Release Date : 1999
Effect Of Sideslip On The Flow Over A 65 Deg Delta Wing written by Nicolaas Verhaagen 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.
Flow-visualization tests, surface-pressure measurements and balance tests were conducted on a model of a flat-plate 65-deg swept delta wing in a low-speed wind tunnel. The model was tested at a fixed angle of attack of 30 deg and at angles of sideslip up to 20 deg. The tests generated data that were used to study the effect of sideslip on the flow over the delta wing.