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Design Guide for Aerodynamics Testing of Earth and Planetary Entry Vehicles in a Ballistic RangeThe purpose of this manual is to aid in the design of an aerodynamics test of an earth or planetary entry capsule in a ballistic range. In this manual, much use is made of the results and experience gained in 50 years of ballistic range aerodynamics testing at the NASA Ames Research Center, and in particular, that gained in the last 27 years, while the author was working at NASA Ames. The topics treated herein include: Data to be obtained; flight data needed to design test; Reynolds number and dynamic similarity of flight trajectory and ballistic range test; capabilities of various ballistic ranges; Calculations of swerves due to average and oscillating lift and of drag-induced velocity decreases; Model and sabot design; materials, weights and stresses; Sabot separation; Launches at angle of attack and slapping with paper to produce pitch/yaw oscillations.
Document ID
20170001991
Acquisition Source
Ames Research Center
Document Type
Technical Memorandum (TM)
Authors
Bogdanoff, David W. (Analytical Mechanics Associates, Inc. Moffett Field, CA, United States)
Date Acquired
March 3, 2017
Publication Date
January 1, 2017
Subject Category
Aerodynamics
Report/Patent Number
ARC-E-DAA-TN20974
NASA/TM-2017-219473
Funding Number(s)
CONTRACT_GRANT: NNA15BB15C
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Test Design
Ballistic Range
Model Design

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