Author : W. LUCHUK
Publisher :
Page : 6 pages
File Size : 18,48 MB
Release : 1953
Category :
ISBN :
A series of tests at M=4.28 was conducted in the 40 x 40 cm aeroballistics tunnel no. 2 using a 0.289-scale model of the Angled Arrow projectile with various nose and tail modifications. From these tests the normal force coefficients (CN), the pitching moment coefficients about the base (C0B) and the axial force coefficients (CA) were obtained. These data are presented. (Extracted from report).
Author : Richmond P. Boyden
Publisher :
Page : 86 pages
File Size : 23,22 MB
Release : 1978
Category : Dynamics
ISBN :
Author : G. L. Winchenback
Publisher :
Page : 54 pages
File Size : 22,8 MB
Release : 1979
Category : Ballistic ranges
ISBN :
Author : J. T. Best (Jr.)
Publisher :
Page : 194 pages
File Size : 44,5 MB
Release : 1974
Category : Drag (Aerodynamics)
ISBN :
Static-force tests were conducted at Mach number 2.25, 3, and 4 on a 0.25 -scale model of the High Altitude Supersonic Target (HAST) missile.
Author : Frank J. Regan
Publisher :
Page : 122 pages
File Size : 22,15 MB
Release : 1971
Category : Ballistics
ISBN :
The report presents the results of ballistics range and wind-tunnel measurements of the static force and moment and the pitch-damping, roll-damping and Magnus moments for a General Purpose 20-Millimeter Projectile. Data are presented for a Smooth and Basic configuration. These aerodynamic data are used in a special digital computer program to rapidly assess the stability of the projectiles over various mission profiles. The normal-force and pitching-moment derivatives are evaluated, theoretically, by Wood's method and compared with the measurements.
Author : J. A. DARLING
Publisher :
Page : 1 pages
File Size : 48,40 MB
Release : 1955
Category :
ISBN :
Author : Thomas R. Yechout
Publisher : AIAA
Page : 666 pages
File Size : 38,33 MB
Release : 2003
Category : Aerodynamics
ISBN : 9781600860782
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Author : Frankie Gale Moore
Publisher :
Page : 218 pages
File Size : 40,12 MB
Release : 1973
Category : Guided missiles
ISBN :
Several theoretical and empirical procedures are combined into a single computer program to predict lift, drag, and center of pressure on quite general wing-body geometries. The method is applicable for Mach number zero to three and angle-of-attack zero to about fifteen degrees. Computed results for several configurations compare well with experimental and other analytical results. It costs about five dollars per Mach number to compute the static aerodynamics of a typical wing-body shape on the CDC 6700 computer.
Author : United States. Army Materiel Command
Publisher :
Page : 148 pages
File Size : 45,76 MB
Release : 1966
Category : Projectiles
ISBN :
Author : I. M. Nestingen
Publisher :
Page : 18 pages
File Size : 40,47 MB
Release : 1951
Category :
ISBN :
This report presents the results of a series of shots fired in the NOL pressurized ballistics firing range to determine the effect of Reynolds number on drag of the Angled Arrow Projectile at Mach numbers of 1.86 and 2.87. Drag values were determined for a Reynolds number variation of nine million. The results obtained at M = 1.86 indicate an increase in drag coefficient of approximately 4.55 per cent for a change in Reynolds number from 2,000,000 to 11,000,000. At M - 2.87 an increase in drag coefficient of approximately 20 percent was obtained for a similar variation in Reynolds number. The drag values are in fair agreement with wind-tunnel tests and with the estimated free-flight values of the full-scale missile at high altitude.
