Sphere-cone-cone Surface Pressure Distribution at Mach Numbers of 5, 6, 8, and 10
Author : R. R. Eaton
Publisher :
Page : 60 pages
File Size : 47,67 MB
Release : 1968
Category : Aerodynamic load
ISBN :
Author : R. R. Eaton
Publisher :
Page : 60 pages
File Size : 47,67 MB
Release : 1968
Category : Aerodynamic load
ISBN :
Author : Robert J. McGhee
Publisher :
Page : 50 pages
File Size : 19,23 MB
Release : 1969
Category : Blunt bodies
ISBN :
Author :
Publisher :
Page : 780 pages
File Size : 12,90 MB
Release :
Category : Science
ISBN :
Author : Juergen W. Heberle
Publisher :
Page : 76 pages
File Size : 29,61 MB
Release : 1949
Category : Cone
ISBN :
Accurate experimental data are given on the shape and the location of detached shock waves on cones and spheres at Mach numbers from 1.17 to 1.81. The data are correlated to obtain equations that describe the shock waves. This knowledge of the shock waves should be useful in calculations of the pressure distribution and the pressure drag of the fore part of cones and spheres. The experimental data on shock waves are compared with theory.
Author : Theodore R. Creel
Publisher :
Page : 42 pages
File Size : 45,8 MB
Release : 1968
Category : Aerodynamic load
ISBN :
Author : David A. Stewart
Publisher :
Page : 20 pages
File Size : 37,48 MB
Release : 1969
Category : Helium
ISBN :
Shock shape and surface pressure measurements on hypersonic pointed cones in helium.
Author : Alfred Merle Morrison
Publisher :
Page : 260 pages
File Size : 41,94 MB
Release : 1975
Category : Aerodynamic load
ISBN :
This report contains numerical tables of aerodynamic coefficients and surface pressure distributions for sphere cone configurations as a function of angle of attack and Mach number. These results were generated by an NSWC/WOL computer code based on a finite difference solution of the steady inviscide three-dimensional compressible flow equation for a perfect gas [upsilon]= 1.4. Cone half angles of 50, 60, 80, 90, 100, 150 and 200 are considered. Truncated values are obtained at axial stations to a length of 200 times the sphere radius, over a Mach number range of 3.5, 5, 10, 20, 25 and 30, for an angle-of-attack span of 10, 30, 50, and 100. Center-of-pressure location, and axial- and normal-force coefficients are tabularly presented at each axial-length increment station. Surface pressure distributions are also presented at each axial-length increment station, including seven meridian plane angles over the half plane from windward to leeward ray. The techniques utilized in generating the tables are described, and comparisons between computed values and values measured in some wind-tunnel experiments are presented. The presentation format is discussed to establish the mechanics necessary to use the tables. The tables are divided into two volumes; the first containing pressure information, and the second, aerodynamic information.
Author :
Publisher :
Page : 286 pages
File Size : 27,21 MB
Release : 1977
Category : Aeronautics
ISBN :
Author : Nickolai Charczenko
Publisher :
Page : 88 pages
File Size : 31,65 MB
Release : 1963
Category : Cone
ISBN :
An investigation was made to determine the drag and stability characteristics of the various decelerators when towed in the wake of several space-vehicle configurations at Mach numbers from 1.57 to 4.65. The following parameters were varied: Reynolds number, trailling distance, ratio of deceleration base diameter to space-vehicle base diameter, cone angle, and size of disk added to the base of a cone.
Author : Society of Automotive Engineers. Committee AC-9, Aircraft Environmental Systems
Publisher :
Page : 778 pages
File Size : 37,70 MB
Release : 1969
Category : Airplanes
ISBN :