Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers
Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers

Author: Frankie Gale Moore

Publisher:

Published: 1972

Total Pages: 146

ISBN-13:

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Several theoretical and empirical methods are comgined into a single computer program to predict lift, drag, and center of pressure on bodies of revolution at subsonic, transonic, and supersonic Mach numbers. The body geometries can be quite general in that pointed, spherically blunt, or truncated noses are allowed as well as discontinuities in nose shape. Particular emphasis is placed on methods which yield accuracies of ninety percent or better for most configurations but yet are computationally fast. theoretical and experimental results are presented for several projectiles and a computer program listing is included an an appendix.

Reynolds Number Effect on Drag of the Angled Arrow Projectile
Reynolds Number Effect on Drag of the Angled Arrow Projectile

Author: I. M. Nestingen

Publisher:

Published: 1951

Total Pages: 18

ISBN-13:

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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.

New Methods for Predicting Nonlinear Lift, Center of Pressure, and Pitching Moment on Middile Configurations
New Methods for Predicting Nonlinear Lift, Center of Pressure, and Pitching Moment on Middile Configurations

Author: Frankie Gale Moore

Publisher:

Published: 1992

Total Pages: 192

ISBN-13:

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A new semiempirical method has been developed to predict normal force, pitching moment, and center of pressure on missile configurations up to angles of attack of 30° The method is based on linear theory and slender body techniques at low angle of attack and uses wind tunnel data to derive nonlinear angle-of-attack corrections as angle of attack increaces. The new improved theories include body alone, wing alone, and body-wing and wing-body interference. While the new theory is databased, simple analytical formulas are derived that allow general use of the techniques. Comparison with the linearized approaches used in the former NSWCDD aeroprediction code shows singificant reductions in errors of aerodynamics above 5° to 10° angle of attack. Limited comparisons to other state-of-the-art engineering codes show the new theory to be as good as or better than anything known to be available for computing planar aerodynamics up to 30° angle of attack.