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Aeroheating Environments for a Mars Smart LanderA proposed Mars Smart Lander is designed to reach the surface via lifting-body atmospheric entry (alpha = 16 deg) to within 10 km of the target site. CFD (computational fluid dynamics) predictions of the forebody aeroheating environments are given for a direct entry from a 2005 launch. The solutions were obtained using an 8-species gas in thermal and chemical nonequilibrium with a radiative-equilibrium wall temperature boundary condition. Select wind tunnel data are presented from tests at NASA Langley Research Center. Turbulence effects are included to account for both smooth body transition and turbulence due to heatshield penetrations. Natural transition is based on a momentum-thickness Reynolds number value of 200. The effects of heatshield penetrations on turbulence are estimated from wind tunnel tests of various cavity sizes and locations. Both natural transition and heatshield penetrations are predicted to cause turbulence prior to the nominal trajectory peak heating time. Laminar and turbulent CFD predictions along the trajectory are used to estimate heat rates and loads. The predicted peak turbulent heat rate of 63 W/sq cm on the heatshield leeward flank is 70% higher than the laminar peak. The maximum integrated heat load for a fully turbulent heat pulse is 38% higher than the laminar load on the heatshield nose. The predicted aeroheating environments with uncertainty factors will be used to design a thermal protection system.
Document ID
20030013001
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Edquist, Karl T. (NASA Langley Research Center Hampton, VA United States)
Liechty, Derek S. (NASA Langley Research Center Hampton, VA United States)
Hollis, Brian R. (NASA Langley Research Center Hampton, VA United States)
Alter, Stephen J. (NASA Langley Research Center Hampton, VA United States)
Loomis, Mark P. (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2002
Subject Category
Space Transportation And Safety
Report/Patent Number
AIAA Paper 2002-4505
Meeting Information
Meeting: AIAA Atmospheric Flight Mechanics Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: August 5, 2002
End Date: August 8, 2002
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

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