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Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 03 And Naca 65a006 Airfoil Section
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Book Synopsis 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 by : Boyd C. Myers
Download or read book 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 published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Joseph Weil
Download or read book Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Joseph Weil and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of an NACA research program, a series of wing-body combinations are being investigated in the Langley high-speed 7- by 10-foot tunnel up to a Mach number of 1.18 utilizing the transonic bump.
Book Synopsis 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 by : Kenneth W. Goodson
Download or read book 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 published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section by : William C. Sleeman
Download or read book 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 published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis 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 by : Thomas J. Jr King
Download or read book 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 published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 6 , Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : William C. Sleeman
Download or read book Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 6 , Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Aifoil Section - Transonic-bump Method by : William C. Jr Sleeman
Download or read book Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Aifoil Section - Transonic-bump Method written by William C. Jr Sleeman and published by . This book was released on 1949 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : William C. Sleeman
Download or read book 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 published by . This book was released on 1949 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis 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 by : Boyd C. Myers
Download or read book 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 published by . This book was released on 1950 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Aerodynamic Characteristics of a Wing with Quarter-chord Swept Back 60 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Thomas J. King
Download or read book Aerodynamic Characteristics of a Wing with Quarter-chord Swept Back 60 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Thomas J. King and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 4, taper ratio 0.6, and NACA 65A006 airfoil section. The results are presented as lift, drag, pitching-moment, and bending moment coefficients for both configurations. The effect of a wing fence on the wing-fuselage characteristics was also investigated. 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. Only a brief analysis is given in order to facilitate the publishing of the data.
Book Synopsis Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0 by : John C. McFall
Download or read book Longitudinal Stability Characteristics at Transonic Speeds of a Rocket-propelled Model of an Airplane Having a 45 Degree Swept Wing of Aspect Ratio 6.0 written by John C. McFall and published by . This book was released on 1954 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-chord Lines Swept Back 45 Degrees, and NACA 63(sub 1)A012 Airfoil Sections by : Edward C. Polhamus
Download or read book Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-chord Lines Swept Back 45 Degrees, and NACA 63(sub 1)A012 Airfoil Sections written by Edward C. Polhamus and published by . This book was released on 1951 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a transonic research program conducted by the National Advisory Committee for Aeronautics, a series of wings is being investigated in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.15 by use of the transonic-bump technique.
Book Synopsis Research Abstracts and Reclassification Notice by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 by : Kenneth P. Spreemann
Download or read book Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Book Synopsis Aerodynamic Characteristics of a 45 Degree Swept-back Wing with Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections by : Anthony J. Proterra
Download or read book Aerodynamic Characteristics of a 45 Degree Swept-back Wing with Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections written by Anthony J. Proterra and published by . This book was released on 1947 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Abstracts by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 442 pages. Available in PDF, EPUB and Kindle. Book excerpt:
