Results Of Flight Tests To Determine The Zero Lift Drag Characteristics Of A 60 Degrees Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6

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Bibliography Of Scientific And Industrial Reports

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Author :
language : en
Publisher:
Release Date : 1956

Bibliography Of Scientific And Industrial 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 1956 with Research categories.

Results Of Flight Tests To Determine The Zero Lift Drag Characteristics Of A 60 Degrees Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6

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Author : Clement J. Welsh
language : en
Publisher:
Release Date : 1951

Results Of Flight Tests To Determine The Zero Lift Drag Characteristics Of A 60 Degrees Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6 written by Clement J. Welsh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with categories.

Results Of Flight Tests To Determine The Zero Lift Drag Characteristics Of A 60 Degree Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6

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Author : Clement J. Welsh
language : en
Publisher:
Release Date : 1950

Results Of Flight Tests To Determine The Zero Lift Drag Characteristics Of A 60 Degree Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6 written by Clement J. Welsh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Aerofoils categories.

Results of an exploratory free-flight investigation at zero-lift of several rocket-powered drag research models equipped with 60 degree swept-back delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.

Result Of A Flight Investigation To Determine The Zero Lift Drag Characteristics Of A 60 Degrees Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6

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Author : Clement J. Welsh
language : en
Publisher:
Release Date : 1956

Result Of A Flight Investigation To Determine The Zero Lift Drag Characteristics Of A 60 Degrees Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6 written by Clement J. Welsh 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.

Results Of A Flight Investigation To Determine The Zero Lift Drag Characteristics Of A 60 Deg Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 1 6

DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1956

Results Of A Flight Investigation To Determine The Zero Lift Drag Characteristics Of A 60 Deg Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 1 6 written by 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.

Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models equipped with 60 deg sweptback delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness. The results of the investigation showed that, of the double-wedge sections with 6 percent thickness, the two sections with positions of maximum thickness at 20 and 50 percent of the chord had drag coefficients approximately equal through the transonic and supersonic Mach number range and had similarly occurring drag rises. The section with position of maximum thickness at 80 percent chord had a drag rise occurring at a Mach number M of approximately 0.15 lower than the drag rise of the other two sections. At M = 1.0, this section had drag coefficients more than twice as large as those of the other two sections; however, this difference decreased with increasing supersonic Mach numbers. The wing drag calculated by the linearized theory was in qualitative agreement with the test results in indicating the effects of varying the position of maximum thickness. The double-wedge section of 5 percent thickness with position of maximum thickness at 50 percent chord had fairly constant drag coefficients throughout the supersonic region, which ranged from about 50 to 80 percent of the drag coefficients for the similar section with twice the thickness ratio. The theoretical wing drag for this section was in very good agreement with the experimental value. The NACA 65-006 airfoil section had lower drag coefficients throughout the test region than any of the double-wedge sections of the same thickness ratio, although at the highest Mach numbers covered by these tests, the differences became very small.

Results Of A Flight Investigation To Determine The Zero Lift Drag Characteristics Of A 60 Degree Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6

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Author : Clement J. Welsh
language : en
Publisher:
Release Date : 1956

Results Of A Flight Investigation To Determine The Zero Lift Drag Characteristics Of A 60 Degree Delta Wing With Naca 65 006 Airfoil Section And Various Double Wedge Sections At Mach Numbers From 0 7 To 1 6 written by Clement J. Welsh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Aerofoils categories.

Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models equipped with 60 deg sweptback delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.

Large Scale Flight Measurements Of Zero Lift Drag And Low Lift Drag Of 10 Wing Body Configurations At Mach Numbers From 0 8 To 1 6

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Author : John D. Morrow
language : en
Publisher:
Release Date : 1953

Large Scale Flight Measurements Of Zero Lift Drag And Low Lift Drag Of 10 Wing Body Configurations At Mach Numbers From 0 8 To 1 6 written by John D. Morrow and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Airplanes categories.

A Note On The Drag Due To Lift Of Delta Wings At Mach Numbers Up To 2 0

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Author : Robert S. Osborne
language : en
Publisher:
Release Date : 1953

A Note On The Drag Due To Lift Of Delta Wings At Mach Numbers Up To 2 0 written by Robert S. Osborne and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Airplanes categories.

Aerodynamic Characteristics Of A Delta Wing With Leading Edge Swept Back 45 Degrees Aspect Ratio 4 And Naca 65a006 Airfoil Section

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Author : William C. Sleeman
language : en
Publisher:
Release Date : 1949

Aerodynamic Characteristics Of A Delta Wing With Leading Edge Swept Back 45 Degrees Aspect Ratio 4 And Naca 65a006 Airfoil Section written by William C. Sleeman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Aerofoils categories.

This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.

Free Flight Measurements Of The Zero Lift Drag Of Several Wings At Mach Numbers From 1 4 To 3 8

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Author : H. Herbert Jackson
language : en
Publisher:
Release Date : 1960

Free Flight Measurements Of The Zero Lift Drag Of Several Wings At Mach Numbers From 1 4 To 3 8 written by H. Herbert Jackson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Mach number categories.