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Favorable Interference Effects On Maximum Lift Drag Ratios Of Half Cone Delta Wing Configurations At Mach 686
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Book Synopsis Favorable Interference Effects on Maximum Lift-drag Ratios of Half-cone Delta-wing Configurations at Mach 6.86 by : David E. Fetterman
Download or read book Favorable Interference Effects on Maximum Lift-drag Ratios of Half-cone Delta-wing Configurations at Mach 6.86 written by David E. Fetterman and published by . This book was released on 1965 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Favorable Interference Effects on Maximum Lift-drag Ratios of Half-cone Delta-wing Configuration at Mach 6.86 by : David E. Fetterman
Download or read book Favorable Interference Effects on Maximum Lift-drag Ratios of Half-cone Delta-wing Configuration at Mach 6.86 written by David E. Fetterman and published by . This book was released on 1965 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Maximum Lift-drag Ratios of Delta-wing by : Patrick J. Johnston
Download or read book Maximum Lift-drag Ratios of Delta-wing written by Patrick J. Johnston and published by . This book was released on 1965 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Lee-surface Volume Addition on Longitudinal Aerodynamics of a High-lift-drag-ratio Wing-body Configuration at Mach 6.0 by : David R. Stone
Download or read book Effects of Lee-surface Volume Addition on Longitudinal Aerodynamics of a High-lift-drag-ratio Wing-body Configuration at Mach 6.0 written by David R. Stone and published by . This book was released on 1968 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Interference Effects on Half-cone Bodies with Thin Wings at Mach 10.03 by : James C. Townsend
Download or read book Aerodynamic Interference Effects on Half-cone Bodies with Thin Wings at Mach 10.03 written by James C. Townsend and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Maximum Lift-drag-ratio Characteristics of Rectangular and Delta Wings at Mach 6.9 by : Jim A. Penland
Download or read book Maximum Lift-drag-ratio Characteristics of Rectangular and Delta Wings at Mach 6.9 written by Jim A. Penland and published by . This book was released on 1965 with total page 52 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 Aerodynamic Interference Effects on Half-cone Bodies with Thin Wings at Mach 10.03 by : James C. Townsend
Download or read book Aerodynamic Interference Effects on Half-cone Bodies with Thin Wings at Mach 10.03 written by James C. Townsend and published by . This book was released on 1970 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Halves of cone bodies having fineness ratios of 2, 4, or 6 were tested with thin flat wings at Mach 10.03 and Reynolds numbers of 1.2X106, 1.5X106, or 1.8X106. Several wing planforms designed empirically or theoretically to match the shape of the shock wave about the body were investigated for each fineness ratio. Tests were also made with thick wings and with wings having various leading-edge shapes. The wing planforms which matched the actual shock shape provide the highest lift-drag ratios. Increasing the fineness ratio of the half-cone body increase the lift-drag ratio but decreases the lift coefficient. Effects of wing thickness and leading-edge shape were very small."--P. [i].
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 1953 with total page 20 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 Interference Effects of Canard Controls on the Longitudinal Aerodynamic Characteristics of a Winged Body at Mach 10 by : Cuyler W. Brooks (Jr.)
Download or read book Interference Effects of Canard Controls on the Longitudinal Aerodynamic Characteristics of a Winged Body at Mach 10 written by Cuyler W. Brooks (Jr.) and published by . This book was released on 1968 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lift-to-drag Ratios of Semispan Delta Wing Configurations at Supersonic and Hypersonic Mach Numbers by : Larry J. Pfaff
Download or read book Lift-to-drag Ratios of Semispan Delta Wing Configurations at Supersonic and Hypersonic Mach Numbers written by Larry J. Pfaff and published by . This book was released on 1968 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 40-in. supersonic and 50-in. hypersonic tunnels of the von Karman Gas Dynamics Facility (VKF) to determine the maximum lift-to-drag ratios of a series of blunt leading edge, semispan delta wings having a 70-deg leading-edge sweep angle. Each wing configuration was comprised of triangular forward and tip panels and a rectangular main wing panel. Data were obtained at Mach numbers from 3 to 8 over an angel-of-attack range from -2 to 14 deg. Testing was primarily at a Reynolds number, based on the maximum wing root chord (48 in.) of 14,400,000 with additional testing at Reynolds numbers of 9,600,000 and 3,400,000. Selected results are presented showing the effect of forward panel bluntness and deflection, and Mach number of the wing lift-to-drag ratios. (Author).
Book Synopsis Effects of Wing Incidence on the Longitudinal Trim Characteristics of a Cambered 70 Deg Delta-wing Configuration at Mach Numbers 3.0 to 5.0 by :
Download or read book Effects of Wing Incidence on the Longitudinal Trim Characteristics of a Cambered 70 Deg Delta-wing Configuration at Mach Numbers 3.0 to 5.0 written by and published by . This book was released on 1960 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Thick Delta Wing Hypersonic Glider Configuration for Angles of Attack Up to 100 Deg by :
Download or read book Static Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Thick Delta Wing Hypersonic Glider Configuration for Angles of Attack Up to 100 Deg written by and published by . This book was released on 1961 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Reduction of Drag Due to Lift at Supersonic Speeds by : Douglas Aircraft Company
Download or read book Reduction of Drag Due to Lift at Supersonic Speeds written by Douglas Aircraft Company and published by . This book was released on 1955 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: $EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Book Synopsis Current Methods for Prediction and Minimization of Lift Induced Drag at Supersonic Speeds by :
Download or read book Current Methods for Prediction and Minimization of Lift Induced Drag at Supersonic Speeds written by and published by . This book was released on 1966 with total page 28 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:
