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Estimation Of The Static Aerodynamic Characteristics Of Ordnance Projectiles At Supersonic Speeds

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Estimation Of The Static Aerodynamic Characteristics Of Ordnance Projectiles At Supersonic Speeds

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Author : Robert L. McCoy
language : en
Publisher:
Release Date : 1973

Estimation Of The Static Aerodynamic Characteristics Of Ordnance Projectiles At Supersonic Speeds written by Robert L. McCoy and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1973 with Aerodynamics, Supersonic categories.

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.

Supersonic Hypersonic Aerodynamics And Heat Transfer For Projectile Design Using Viscous Inviscid Interaction

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Author : Michael J. Nusca
language : en
Publisher:
Release Date : 1990

Supersonic Hypersonic Aerodynamics And Heat Transfer For Projectile Design Using Viscous Inviscid Interaction written by Michael J. Nusca and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamic heating categories.

An aerodynamic design code for axisymmetric projectiles has been developed using a viscous-inviscid interaction scheme. Separate solution procedures for inviscid (Euler) and viscous (boundary layer) flowfields are coupled by an iterative solution procedure. This code yields body surface flow profiles in less than one minute of run time on minicomputers. These surface profiles represent converged solutions to both the inviscid and viscous equations. the capability of computing local reverse flow regions is included. The procedure is formulated for supersonic and hypersonic Mach numbers including both laminar and turbulent flow. In addition, aerodynamic heating equations are used to compute heat transfer coefficient and local Stanton number from flow profiles. Computed surface pressure profiles for Mach numbers 2 thru 6 are compared to wind tunnel measurements on cone-cylinder-flare projectiles. Computed surface heat transfer coefficients are compared to results obtained from wind tunnel measurements on cone-cylinder-flare, flat plate, and blunt-cone models at Mach numbers 5 and 10. Keywords: Hypersonic flow; Computational aerodynamics; Boundary layers; Heat transfer; Projectile design.

Scientific And Technical Aerospace Reports

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Author :
language : en
Publisher:
Release Date : 1974

Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Aeronautics categories.

Mc Drag A Computer Program For Estimating The Drag Coefficients Of Projectiles

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Author : Robert L. McCoy
language : en
Publisher:
Release Date : 1981

Mc Drag A Computer Program For Estimating The Drag Coefficients Of Projectiles written by Robert L. McCoy and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1981 with Drag (Aerodynamics) categories.

This report presents a FORTRAN program "MC DRAG" for estimating a projectile's zero-yaw drag coefficient from the given values of certain size and shape parameters. The results are valid over a Mach number range of 0.5 to 5 and a projectile diameter range of 4 to 400 millimetres. A user's guide and a FORTRAN listing of MC DRAG is provided. The program is applied to three illustrative examples: (1) an experimental low-drag small arms bullet, the 5. 56mm BRL-1 design; (2) a 55mm scale model of the Minuteman re-entry stage vehicle; (3) the 155mm long-range artillery shell M549. The MC DRAG program estimates drag coefficient to within 3% error at supersonic speeds, 11% error at transonic speeds, and 6% error at subsonic speeds.

Ordnance Corps Pamphlet

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Author : United States. Army. Ordnance Corps
language : en
Publisher:
Release Date : 1957

Ordnance Corps Pamphlet written by United States. Army. Ordnance Corps and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with categories.

Design For Control Of Projectile Flight Characteristics

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Author : United States. Army Materiel Command
language : en
Publisher:
Release Date : 1966

Design For Control Of Projectile Flight Characteristics written by United States. Army Materiel Command and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Projectiles, Aerial categories.

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.