Author : Thomas N. Canning
Publisher :
Page : 22 pages
File Size : 24,67 MB
Release : 1954
Category : Aerodynamics, Hypersonic
ISBN :
Author :
Publisher :
Page : 404 pages
File Size : 47,23 MB
Release : 1965
Category :
ISBN :
Author : United States. National Aeronautics and Space Administration
Publisher :
Page : pages
File Size : 14,14 MB
Release : 1960-07
Category :
ISBN :
Author : E. Leon Morrisette
Publisher :
Page : 36 pages
File Size : 46,76 MB
Release : 1965
Category : Guided missiles
ISBN :
Author : William Letko
Publisher :
Page : 22 pages
File Size : 36,28 MB
Release : 1960
Category : Lift (Aerodynamics)
ISBN :
Author : United States. National Aeronautics and Space Administration
Publisher :
Page : 448 pages
File Size : 32,65 MB
Release : 1960
Category : Aeronautics
ISBN :
Author : Daniel W. Lester
Publisher :
Page : 690 pages
File Size : 12,82 MB
Release : 1980
Category : Government publications
ISBN :
Author : Vernard E. Lockwood
Publisher :
Page : 36 pages
File Size : 32,61 MB
Release : 1960
Category :
ISBN :
Author : Earl D. Knechtel
Publisher :
Page : 36 pages
File Size : 45,45 MB
Release : 1956
Category : Charts, diagrams, etc
ISBN :
An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Author : I. M. Nestingen
Publisher :
Page : 18 pages
File Size : 48,17 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.
