Download or read book The Effect of Inlet Installation on the Zero lift Drag of a 60 Degree 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 1955 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book The Zero lift Drag of a 60 degrees Delta wing body Combination AGARD Model 2 Obtained from Free flight Tests Between Mach Numbers of 0 8 and 1 7 written by Robert O. Piland and published by . This book was released on 1954 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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:
Download or read book The Zero lift Drag of a 60 Degree Delta wing body Combination AGARD Model 2 Obtained from Free flight Tests Between Mach Numbers of 0 8 and 1 7 written by Robert O. Piland and published by . This book was released on 1954 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD Model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4,000,000 and 12,000,000, respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good.
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:
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:
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.
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:
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:
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:
Download or read book Missile Aerodynamics written by Jack Norman Nielsen and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 1988-01-01 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt: The similarities between the airplane and the missile extend beyond their flying capabilities, and at higher operational speeds, the configuration distinctions become even less apparent. " Missile Aerodynamics," a classic now available from AIAA and Nielsen Engineering and Research, Inc., combines the best of missile and airplane aerodynamics, drawing extensively from numerous technical papers to present a rational and unified account of the principles behind missile projection. Evaluate the missile versus the airplane in a multitude of areas, from longitudinal acceleration, wing loading, roll and dynamic stability, guidance and navigation, and more. J.N. Nielsen covers every aspect of missile aerodynamics, from the classification of missiles and basic formulas to innovative aerodynamic controls. In one reliable reference, readers will find hundreds of schematics, equations, and tables with practical applications in missile design and engineering. Originally published by Nielsen Engineering and Research, Inc.
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:
Download or read book Zero lift Drag of a Large Fuselage Cavity and a Partially Submerged Store on a 52 5 Sweptback wing body Configuration as Determined from Free flight Tests at Mach Numbers of 0 7 to 1 53 written by Sherwood Hoffman and published by . This book was released on 1957 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Effect of External Stores on the Stability and Control Characteristics of a Delta Wing Fighter Model at Mach Numbers from 0 60 to 2 01 written by and published by . This book was released on 1983 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
