Aerodynamic Characteristics Of Four Wings Of Sweepback Angles 0 Degrees 35 Degrees 45 Degrees And 60 Degrees Naca 65a006 Airfoil Section Aspect Ratio 4 And Taper Ratio 0 6 In Combination With A Fuselage At High Subsonic Mach Numbers And At A Mach Number Of 1 2
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Aerodynamic Studies
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Author : Zbiginew Krzywoblocki
language : en
Publisher:
Release Date : 1957
Aerodynamic Studies written by Zbiginew Krzywoblocki and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerodynamics categories.
Aerodynamic Characteristics Of Four Wings Of Sweepback Angles 0 Degrees 35 Degrees 45 Degrees And 60 Degrees Naca 65a006 Airfoil Section Aspect Ratio 4 And Taper Ratio 0 6 In Combination With A Fuselage At High Subsonic Mach Numbers And At A Mach Number Of 1 2
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Author : Arvo A. Luoma
language : en
Publisher:
Release Date : 1951
Aerodynamic Characteristics Of Four Wings Of Sweepback Angles 0 Degrees 35 Degrees 45 Degrees And 60 Degrees Naca 65a006 Airfoil Section Aspect Ratio 4 And Taper Ratio 0 6 In Combination With A Fuselage At High Subsonic Mach Numbers And At A Mach Number Of 1 2 written by Arvo A. Luoma 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.
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 3 And Naca 65a006 Airfoil Section
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Author : Boyd C. Myers
language : en
Publisher:
Release Date : 1949
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 3 And Naca 65a006 Airfoil Section written by Boyd C. Myers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Airplane categories.
This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, 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 were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 And Naca 65a006 Airfoil Section
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Author : William C. Sleeman
language : en
Publisher:
Release Date : 1949
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 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 Aerodynamics, Transonic categories.
Investigation Of The Aerodynamic Characteristics In Pitch And Sideslip Of A 45 Swept Wing Airplane Configuration With Various Vertical Locations Of The Wing And Horizontal Tail
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1957
Investigation Of The Aerodynamic Characteristics In Pitch And Sideslip Of A 45 Swept Wing Airplane Configuration With Various Vertical Locations Of The Wing And Horizontal Tail written by M. Leroy Spearman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 60 Degrees Aspect Ratio 2 Taper Ratio 0 6 And Naca 65a006 Airfoil Section
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Author : Boyd C. Myers
language : en
Publisher:
Release Date : 1950
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 60 Degrees Aspect Ratio 2 Taper Ratio 0 6 And Naca 65a006 Airfoil Section written by Boyd C. Myers and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Airplanes categories.
This paper presents the results of the investigation of a wing-alone and a wing-fuselage configuration employing a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section. The results are presented as lift, drag, pitching-moment and bending-moment coefficients for both configurations. In addition, effective downwash angles and point dynamic pressures for a range of tail heights at a probable tail length are presented for the two configurations investigated.
Effects Of Spanwise Thickness Variation On The Transonic Aerodynamic Characteristics Of Wings Having 35 Degrees Of Sweepback Aspect Ratio 4 And Taper Ratio 0 60
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Author : William D. Morrison
language : en
Publisher:
Release Date : 1951
Effects Of Spanwise Thickness Variation On The Transonic Aerodynamic Characteristics Of Wings Having 35 Degrees Of Sweepback Aspect Ratio 4 And Taper Ratio 0 60 written by William D. Morrison and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aerodynamics, Transonic categories.
An investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of a spanwise variation in thickness ratio on the aerodynamic characteristics of a wing having a plan form identical to that of a constant-percent thickness-ratio wing previously investigated as part of an extensive transonic research program. The wing with thickness variation had 35 degrees of sweepback, aspect ratio 4, and taper ratio 0.60, with airfoil section (parallel to the free stream) tapered from an NACA 65A006 section at root chord to an NACA 65A002 section at the tip chord. The test Mach number range was from 0.60 to 1.08 at Reynolds numbers of the order 0f 650,000.
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35 Degrees Aspect Ratio 4 Taper Ratio 0 6 And Naca 65a006 Airfoil Section
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Author : William C. Sleeman
language : en
Publisher:
Release Date : 1949
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35 Degrees Aspect Ratio 4 Taper Ratio 0 6 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 Aerodynamics, Transonic categories.
This paper presents the results of the investigation of a wing-alone and a wing-fuselage combination employing a wing with the quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for the wing-alone and wing-body configurations. Effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also 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.
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 60 Degrees Aspect Ratio 4 Taper Ratio 0 6 And Naca 65a006 Airfoil Section Transonic Bump Method
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Author : Thomas J. Jr King
language : en
Publisher:
Release Date : 1949
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 60 Degrees Aspect Ratio 4 Taper Ratio 0 6 And Naca 65a006 Airfoil Section Transonic Bump Method written by Thomas J. Jr King and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with categories.
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 45 Degrees Aspect Ratio 6 Taper Ratio 0 6 And Naca 65a006 Airfoil Section
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Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1949
Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 45 Degrees Aspect Ratio 6 Taper Ratio 0 6 And Naca 65a006 Airfoil Section written by Kenneth W. Goodson 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 a wing-alone and a wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, 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 configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.