Download or read book Summary of Aerodynamic Characteristics of a Winged Reentry Vehicle at Mach Numbers from 0 06 to 9 6 with Detailed Results at a Mach Number of 9 6 written by and published by . This book was released on 1963 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Group of Winged Reentry Vehicles at Mach Number 6 01 at Angles of Attack from 60 to 120 and 10 to 30 Roll at 90 Angle of Attack written by James G. Hondros and published by . This book was released on 1961 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Aerodynamic Characteristics of Several High drag Bodies at Mach Numbers from 1 50 to 4 63 written by James F. Campbell and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Stability and Control Characteristics of a Proposed Winged Reentry Vehicle at Mach Numbers of 1 50 2 96 and 4 63 written by and published by . This book was released on 1962 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Aerodynamic Characteristics at Mach Numbers from 0 50 to 1 19 of a Supersonic Transport Model with a Modified M Wing written by Edward J. Ray and published by . This book was released on 1967 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Group of Winged Reentry Vehicles at Mach Number 6 01 at Angles of Attack from 60 Deg to 120 Deg and Minus 10 Deg to 30 Deg Roll at 90 Deg Angle of Attack written by and published by . This book was released on 1961 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics at Mach Numbers of 1 5 1 8 and 2 0 of a Blended Wing body Configuration with and Without Integral Canards written by A. Warner Robins and published by . This book was released on 1979 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics Over a Mach Number Range of 1 40 to 2 78 of a Rocket propelled Airplane Configuration Having a Low 52 20 Delta Wing and an Unswept Horizontal Tail written by Alan B. Kehlet and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1996 with total page 948 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Aerodynamic Characteristics at a Mach Number of 1 97 of a Series of Related Winged Reentry Configurations for Angles of Attack from 0 to 90 written by Gerald V. Foster and published by . This book was released on 1961 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics Over a Mach Number Range of 1 40 to 2 78 of a Rocket propelled Airplane Configuration Having a Low 52 2 Delta Wing and an Unswept Horizontal Tail written by Alan B. Kehlet and published by . This book was released on 1958 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Aerodynamic Characteristics at Mach Numbers from 0 40 to 1 10 of a Blunted Right trangular Pyramidal Lifting Reentry Configuration Employing Variable sweep Wing Panels written by Bernard Spencer and published by . This book was released on 1963 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Longitudinal Aerodynamic Characteristics at a Mach Number of 1 97 of a Series of Related Winged Reentry Configurations for Angles of Attack from 0 Deg to 90 Deg written by and published by . This book was released on 1961 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics at Mach Numbers from 1 50 to 4 63 of a Variable geometry Lifting Reentry Concept Employing Elevator and Body Base Flaps for Control written by Roger H. Fournier and published by . This book was released on 1967 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of a lifting body configuration has been conducted in the Langley Unitary Plan wind tunnel through a Mach number range from 1.50 to 4.63 to determine the control effectiveness characteristics of body base flaps with and without anhedral tail elevator controls.
Download or read book Effects of Several Nose and Vertical fin Modifications on the Low angle of attack Static Stability of a Winged Reentry Vehicle at Mach Numbers of 9 6 in Air and 17 8 in Helium written by and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Aerodynamic Characteristics of a Winged Single stage to orbit Vehicle at Mach Numbers from 0 3 to 4 63 written by and published by . This book was released on 1978 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Loading Characteristics at Mach Numbers from 0 80 to 1 20 of a 1 10 scale Three stage Scout Model written by Thomas C. Kelly and published by . This book was released on 1961 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic loads results have been obtained in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.80 to 1.20 for a 1/10-scale model of the upper three stages of the Scout vehicle. Tests were conducted through an angle-of-attack range from -8° to 8° at an average test Reynolds number per foot of about 4.0 x 106. Results indicated that the peak negative pressures associated with expansion corners at the nose and transition flare exhibit sizeable variations which occur over a relatively small Mach number range. The magnitude of the variations may cause the critical local loading condition for the full-scale vehicle to occur at a Mach number considerably lower than that at which the maximum dynamic pressure occurs in flight. The addition of protuberances simulating antennas and wiring conduits had slight, localized effects. The lift carryover from the nose and transition flare on the cylindrical portions of the model generally increased with an increase in Mach number.
