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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 07 16
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Book Synopsis 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 by :
Download or read book 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 published by . This book was released on 1956 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis 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 by : Clement J. Welsh
Download or read book 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 published by . This book was released on 1956 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis 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 by : Clement J. Welsh
Download or read book 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 published by . This book was released on 1956 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Clement J. Welsh
Download or read book 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 published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Clement J. Welsh
Download or read book 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 published by . This book was released on 1950 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 by : Robert S. Osborne
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Measured and Predicted Section Wave Drag Coefficients at a Mach Number of 1.6 for a Delta Wing with Two Airfoil Sections by : Frederick C. Grant
Download or read book Measured and Predicted Section Wave Drag Coefficients at a Mach Number of 1.6 for a Delta Wing with Two Airfoil Sections written by Frederick C. Grant and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : John D. Morrow
Download or read book 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 published by . This book was released on 1953 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Some Section Modifications and Protuberances on the Zero-lift Drag of Delta Wings at Transonic and Supersonic Speeds by : Carl A. Sandahl
Download or read book Effect of Some Section Modifications and Protuberances on the Zero-lift Drag of Delta Wings at Transonic and Supersonic Speeds written by Carl A. Sandahl and published by . This book was released on 1954 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Investigation to Obtain Drag-at-lift and Stability Data for a 60 Degree Delta-wing-body Configuration Over a Mach Number Range of 1.3 to 1.6 by : Clement J. Welsh
Download or read book Free-flight Investigation to Obtain Drag-at-lift and Stability Data for a 60 Degree Delta-wing-body Configuration Over a Mach Number Range of 1.3 to 1.6 written by Clement J. Welsh and published by . This book was released on 1955 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight tests have been made of a rocket-propelled 60 degree delta-wing-body configuration; the wing airfoil section was NACA 0003-63. Drag at lift and stability data were obtained for a Mach number range of 1.28 to 1.6.
Book Synopsis Aerodynamic Characteristics of Two Delta Wings and Two Trapezoidal Wings at Mach Number of 4.04 by : Robert W. Dunning
Download or read book Aerodynamic Characteristics of Two Delta Wings and Two Trapezoidal Wings at Mach Number of 4.04 written by Robert W. Dunning and published by . This book was released on 1953 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Drag Due to Lift at Mach Numbers Up to 2.0 by : Edward C. Polhamus
Download or read book Drag Due to Lift at Mach Numbers Up to 2.0 written by Edward C. Polhamus and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Two Leading-edge Modifications on the Aerodynamic Characteristics of a Thin Low-aspect-ratio Delta Wing at Transonic Speeds by : John P. Mugler
Download or read book Effects of Two Leading-edge Modifications on the Aerodynamic Characteristics of a Thin Low-aspect-ratio Delta Wing at Transonic Speeds written by John P. Mugler and published by . This book was released on 1956 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 8-foot transonic tunnel to determine the aerodynamic characteristics of a thin 60 degree delta wing with two leading-edge modifications (conical leading-edge camber and leading-edge droop) in combination with bodies with and without body indentation in accordance with the transonic-area-rule concept. The tests covered a Mach number range from 060 to 1.15 and an angle-of-attack range from -4 to 20 degrees at a Reynolds number of about 3,000,000 based on the wing mean aerodynamic chord. The wing had an aspect ratio of 2.31, a taper ratio of 0, and, without modifications, had NACA 65A003 airfoil sections parallel to the model plane of symmetry.
Book Synopsis The Effect of Inlet Installation of the Zero-lift Drag of a 60° Delta-wing-body Configuration from Flight Tests at Mach Numbers from 0.8 to 1.86 by : Charles F. Merlet
Download or read book The Effect of Inlet Installation of the Zero-lift Drag of a 60° Delta-wing-body Configuration from Flight Tests at Mach Numbers from 0.8 to 1.86 written by Charles F. Merlet and published by . This book was released on 1958 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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