Missile Aerodynamics (Aerodynamique Des Missiles).
Author | : |
Publisher | : |
Total Pages | : 507 |
Release | : 1998 |
Genre | : |
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Author | : |
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Total Pages | : 507 |
Release | : 1998 |
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Total Pages | : |
Release | : 1950 |
Genre | : |
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Author | : |
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Total Pages | : 360 |
Release | : 1965 |
Genre | : Aeronautics |
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Author | : |
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Total Pages | : 356 |
Release | : 1974 |
Genre | : Aerodynamics |
ISBN | : |
Author | : Frankie Gale Moore |
Publisher | : |
Total Pages | : 148 |
Release | : 1997 |
Genre | : Aerodynamics |
ISBN | : |
Author | : Jack Norman Nielsen |
Publisher | : AIAA (American Institute of Aeronautics & Astronautics) |
Total Pages | : 450 |
Release | : 1988-01-01 |
Genre | : Guided missiles |
ISBN | : 9780962062902 |
The similarities between the airplane and the missile extend beyond their flying capabilities, and at higher operational speeds, the configuration distinctions become even less apparent. " Missile Aerodynamics," a classic now available from AIAA and Nielsen Engineering and Research, Inc., combines the best of missile and airplane aerodynamics, drawing extensively from numerous technical papers to present a rational and unified account of the principles behind missile projection. Evaluate the missile versus the airplane in a multitude of areas, from longitudinal acceleration, wing loading, roll and dynamic stability, guidance and navigation, and more. J.N. Nielsen covers every aspect of missile aerodynamics, from the classification of missiles and basic formulas to innovative aerodynamic controls. In one reliable reference, readers will find hundreds of schematics, equations, and tables with practical applications in missile design and engineering. Originally published by Nielsen Engineering and Research, Inc.
Author | : |
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Total Pages | : 352 |
Release | : 1994 |
Genre | : Guided missiles |
ISBN | : 9789283507529 |
Author | : Mark Pinney |
Publisher | : McGraw-Hill Professional |
Total Pages | : 0 |
Release | : 2013-12-29 |
Genre | : Technology & Engineering |
ISBN | : 9780071831321 |
Proven techniques for deriving the basic aerodynamic properties of axisymmetric-shaped bodies with the minimum amount of time and effort Aerodynamics of Missiles and Rockets describes the basic aerodynamics model used in the widespread Analytical Initial Missile Synthesis (AIMS) computer code for symmetric missile and rocket sizing and design. It is a collection of empirical, semi-empirical and theoretical aerodynamics engineering methods for a component build-up approach to aerodynamics prediction. This book serves as an on-the-job application manual and desk reference for the prediction of basic aerodynamics. It can also be used for courses in applied aerodynamics in Mechanical and Aerospace Engineering programs and for short courses in industry and government. This practical guide provides an alternative approach to utilizing numerous, complex, stand-alone computer codes, but is also a good complement to these codes. The book offers insight into the methods and techniques used to derive answers and correct magnitudes generated by code, giving confidence in final results. Features a Microsoft Excel file that automates calculations and provides complete tabulated output for missile and rocket geometry and design, and design and for rapid assessments of aerodynamic properties based on changes in geometry or flight conditions On-the-job application manual and desk reference for the prediction of basic aerodynamics Combination of long-standing, empirical and semi-empirical techniques with classical aerodynamic theory A component build-up approach utilized, with body and wing/tail surface aerodynamics determined separately and then combined for total configuration zero-lift drag, lift, center of pressure location, and pitching moment
Author | : United States. Army Materiel Command |
Publisher | : |
Total Pages | : 108 |
Release | : 1965 |
Genre | : Aerodynamics |
ISBN | : |
Author | : James DeSpirito |
Publisher | : |
Total Pages | : 212 |
Release | : 2004 |
Genre | : Computational fluid dynamics |
ISBN | : |
Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.