NDLI: Blunt body aerodynamics for hypersonic low density flows

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Blunt body aerodynamics for hypersonic low density flows

Content Provider	NASA Technical Reports Server (NTRS)
Author	Greene, Francis A. Moss, James N. Glass, Christopher E.
Copyright Year	2006
Description	Numerical simulations are performed for the Apollo capsule from the hypersonic rarefied to the continuum regimes. The focus is on flow conditions similar to those experienced by the Apollo 6 Command Module during the high altitude portion of its reentry. The present focus is to highlight some of the current activities that serve as a precursor for computational tool assessments that will be used to support the development of aerodynamic data bases for future capsule flight environments, particularly those for the Crew Exploration Vehicle (CEV). Results for aerodynamic forces and moments are presented that demonstrate their sensitivity to rarefaction; that is, free molecular to continuum conditions. Also, aerodynamic data are presented that shows their sensitivity to a range of reentry velocities, encompassing conditions that include reentry from low Earth orbit, lunar return, and Mars return velocities (7.7 to 15 km/s). The rarefied results obtained with direct simulation Monte Carlo (DSMC) codes are anchored in the continuum regime with data from Navier-Stokes simulations.
File Size	393637
Page Count	6
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20060028188
Archival Resource Key	ark:/13960/t8bg7nm0h
Language	English
Publisher Date	2006-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Navier-stokes Equation Low Density Flow Command Modules Hypersonic Flow Blunt Bodies Computerized Simulation Data Simulation Monte Carlo Method Rarefied Gas Dynamics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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