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Wind Tunnel Investigation At Mach Numbers From 147 To 462 Of Static Aerodynamic Characteristics Of Twelve Nose Cones Designed For Supersonic Impact
Download Wind Tunnel Investigation At Mach Numbers From 147 To 462 Of Static Aerodynamic Characteristics Of Twelve Nose Cones Designed For Supersonic Impact full books in PDF, epub, and Kindle. Read online Wind Tunnel Investigation At Mach Numbers From 147 To 462 Of Static Aerodynamic Characteristics Of Twelve Nose Cones Designed For Supersonic Impact ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 1.47 to 4.62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact by :
Download or read book Wind-tunnel Investigation at Mach Numbers from 1.47 to 4.62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact written by and published by . This book was released on 1961 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Wind Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Five Nose Cones Designed for Supersonic Impact by : John P. Jr Mugler
Download or read book Transonic Wind Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Five Nose Cones Designed for Supersonic Impact written by John P. Jr Mugler and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation at Mach Numbers from 1.47 to 2.87 of Static Stability Characteristics of Nine Nose Cones Designed for Supersonic Impact Velocities by :
Download or read book An Investigation at Mach Numbers from 1.47 to 2.87 of Static Stability Characteristics of Nine Nose Cones Designed for Supersonic Impact Velocities written by and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations by : Albin O. Pearson
Download or read book Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by Albin O. Pearson and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of the Redstone "B" Nose Cone at Mach Numbers from 1.75 to 5.00 by : Maurice A. Sylvester
Download or read book Wind Tunnel Tests of the Redstone "B" Nose Cone at Mach Numbers from 1.75 to 5.00 written by Maurice A. Sylvester and published by . This book was released on 1963 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 0.40 to 1.14 of the Static Aerodynamic Characteristics of a Nonlifting Vehicle Suitable for Reentry by : Albin O. Pearson
Download or read book Wind-tunnel Investigation at Mach Numbers from 0.40 to 1.14 of the Static Aerodynamic Characteristics of a Nonlifting Vehicle Suitable for Reentry written by Albin O. Pearson and published by . This book was released on 1959 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 0.20 to 1.17 of the Static Aerodynamic Characteristics of a Possible Reentry Capsule by :
Download or read book Wind-tunnel Investigation at Mach Numbers from 0.20 to 1.17 of the Static Aerodynamic Characteristics of a Possible Reentry Capsule written by and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation at Mach Numbers from 0.20 to 4.63 of the Aerodynamic Performance, Static Stability, and Trimming Characteristics of a Canard Configuration Designed for Efficient Supersonic Cruise Flight by :
Download or read book An Investigation at Mach Numbers from 0.20 to 4.63 of the Aerodynamic Performance, Static Stability, and Trimming Characteristics of a Canard Configuration Designed for Efficient Supersonic Cruise Flight written by and published by . This book was released on 1961 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Wind-tunnel Investigation of Effects of Noise Bluntness, Face Shape, and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90 by :
Download or read book A Wind-tunnel Investigation of Effects of Noise Bluntness, Face Shape, and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90 written by and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations by :
Download or read book Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Characteristics of Major Active Wind Tunnels at the Langley Research Center by : William T. Schaefer
Download or read book Characteristics of Major Active Wind Tunnels at the Langley Research Center written by William T. Schaefer and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains a brief description of each of the major active wind tunnels at the Langley Research Center.
Book Synopsis Damping in Pitch and Static Stability of Supersonic Impact Nose Cones, Short Blunt Subsonic Impact Nose Cones, and Manned Reentry Capsules at Mach Numbers from 1.93 to 3.05 by : Herman S. Fletcher
Download or read book Damping in Pitch and Static Stability of Supersonic Impact Nose Cones, Short Blunt Subsonic Impact Nose Cones, and Manned Reentry Capsules at Mach Numbers from 1.93 to 3.05 written by Herman S. Fletcher and published by . This book was released on 1960 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Wind Tunnel Investigation of Effects of Nose Bluntness, Face Shape, and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.93, and 3.90 by : Fred L. Smith
Download or read book A Wind Tunnel Investigation of Effects of Nose Bluntness, Face Shape, and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.93, and 3.90 written by Fred L. Smith and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Reynolds Number and Model Support on the Supersonic Aerodynamic Chacteristics of a 140° Included-angle Cone by : Charles D. Trescot
Download or read book Effects of Reynolds Number and Model Support on the Supersonic Aerodynamic Chacteristics of a 140° Included-angle Cone written by Charles D. Trescot and published by . This book was released on 1974 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley Unitary Plan wind tunnel to determine the effects of Reynolds number and sting-support interference on the static aerodynamic characteristics of a 140 deg-included-angle cone. Base pressures and forces and moments of the model were measured at Mach numbers of 1.50, 2.00, 2.94, and 4.00 for ratios of sting diameter to model diameter that varied from 0.125 to 0.500 through an angle-of-attack range from about minus 4 deg to 13 deg. The Reynolds number, based on model diameter 4.80 in. was varied from 161,000 to 415,000.
Book Synopsis Wind Tunnel Investigation at Mach Numbers from 0.20 to 1.17 of the Static Aerodynamic Characterictics of a Possible Reentry Capsule by : Albin O. Pearson
Download or read book Wind Tunnel Investigation at Mach Numbers from 0.20 to 1.17 of the Static Aerodynamic Characterictics of a Possible Reentry Capsule written by Albin O. Pearson and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Aerodynamic Effects of External Combustion Below Flat-plate Model in 10- by 10-foot Wind Tunnel at Mach 2.4 by : Robert G. Dorsch
Download or read book Investigation of Aerodynamic Effects of External Combustion Below Flat-plate Model in 10- by 10-foot Wind Tunnel at Mach 2.4 written by Robert G. Dorsch and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Wind Tunnel Measurements of Static and Magnus Aerodynamic Coefficients for Projectile Shapes with Tangent and Secant Ogive Noses by : Charles John Nietubicz
Download or read book Supersonic Wind Tunnel Measurements of Static and Magnus Aerodynamic Coefficients for Projectile Shapes with Tangent and Secant Ogive Noses written by Charles John Nietubicz and published by . This book was released on 1980 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests have been conducted for a series of projectile configurations. The shapes tested include a three caliber secant ogive nose and three caliber tangent ogive nose configuration. The overall model length was fixed at 6 calibers for all configurations tested. Static and Magnus aerodynamic coefficient data were obtained at Mach numbers 2.0, 3.0 and 4.0 for angles of attack up to 10.0 deg. The data are presented in graphical form along with tabulations of the summary data. The tangent ogive nose produced a slight increase in the Magnus moment coefficient when compared to similar secant ogive configurations. The boattail configuration, when compared to the cylinder shapes, was found to increase the Magnus moment; however, this effect was shown to decrease with increasing Mach number.
