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Missile Aerodynamics for Ascent and Re-entry
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Author and Affiliation:
Watts, Gaines L.(Jacobs Engineering Group, Inc., Huntsville, AL, United States);
McCarter, James W.(Jacobs Engineering Group, Inc., Huntsville, AL, United States)
Abstract: Aerodynamic force and moment equations are developed for 6-DOF missile simulations of both the ascent phase of flight and a tumbling re-entry. The missile coordinate frame (M frame) and a frame parallel to the M frame were used for formulating the aerodynamic equations. The missile configuration chosen as an example is a cylinder with fixed fins and a nose cone. The equations include both the static aerodynamic coefficients and the aerodynamic damping derivatives. The inclusion of aerodynamic damping is essential for simulating a tumbling re-entry. Appended information provides insight into aerodynamic damping.
Publication Date: Nov 01, 2012
Document ID:
20130003336
(Acquired Jan 28, 2013)
Subject Category: AERODYNAMICS
Report/Patent Number: NASA/CR-2012-217475, M-1351
Document Type: Technical Report
Contract/Grant/Task Num: NNM12AA41C
Financial Sponsor: NASA Marshall Space Flight Center; Huntsville, AL, United States
Organization Source: Jacobs Engineering Group, Inc.; Huntsville, AL, United States
Description: 28p; In English; Original contains color illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution under U.S. Government purpose rights; under NASA contract NNM12AA41C
NASA Terms: AERODYNAMIC CHARACTERISTICS; AERODYNAMIC COEFFICIENTS; AERODYNAMIC FORCES; AERODYNAMICS; ASCENT; DAMPING; FINS; MATHEMATICAL MODELS; MISSILE CONFIGURATIONS; MISSILES; REENTRY; SIMULATION; TUMBLING MOTION
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