Some Aerodynamic Effects Of Varying The Body Length And Head Length Of A Spinning Projectile PDF Download

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Some Aerodynamic Effects of Varying the Body Length and Head Length of a Spinning Projectile

Some Aerodynamic Effects of Varying the Body Length and Head Length of a Spinning Projectile
Author: Elizabeth R. Dickinson
Publisher:
Total Pages: 30
Release: 1965
Genre: Projectiles, Aerial
ISBN:

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Experimental results are presented on the effect, at supersonic velocities, on the drag coefficient, overturning moment coefficient, normal force coefficient and center of pressure, of varying the head length and body length of spinning projectiles. (Author).


Design for Control of Projectile Flight Characteristics

Design for Control of Projectile Flight Characteristics
Author: United States. Army Materiel Command
Publisher:
Total Pages: 290
Release: 1966
Genre: Projectiles, Aerial
ISBN:

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This handbook presents a general survey of the principal factors affecting the flight of projectiles, and describes the methods commonly used for predicting and influencing the flight performance. The coefficients which characterize the aerodynamic forces and moments of a moving body are identified, methods for determining the coefficients applicable to a projectile having a given shape and center of gravity location are described, and the coefficients of a number of projectiles and projectile shapes are given. The use of aerodynamic coefficients in predicting stability, range and accuracy is described. The effects of variations in projectile shape and center of gravity location on range, accuracy and lethality are discussed. Some material on prototype testing and the effects of round-to-round variations in production lots is presented.


Estimation of the Static Aerodynamic Characteristics of Ordnance Projectiles at Supersonic Speeds

Estimation of the Static Aerodynamic Characteristics of Ordnance Projectiles at Supersonic Speeds
Author: Robert L. McCoy
Publisher:
Total Pages: 82
Release: 1973
Genre: Aerodynamics, Supersonic
ISBN:

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A simplified flow field solution has been programmed in an attempt to improve the accuracy of estimates of the static aerodynamic characteristics of ordnance projectiles. It provides estimates of drag, normal force, static moment, and roll damping moment for pointed bodies of revolution at supersonic speed. The program combines the Van Dyke hybrid theory for potential flow, the Van Driest compressible turbulent boundary layer theory, and the Chapman-Sternberg model for supersonic base pressure. Good agreement is demonstrated between the theoretical and experimental data.