NASA's Low Density Supersonic Decelerator Program is developing new technologies that will enable the landing of heavier payloads in low density environments, such as Mars. A recent flight experiment conducted high above the Hawaiian Islands has demonstrated the performance of several decelerator technologies. In particular, the deployment of the Robotic class Supersonic Inflatable Aerodynamic Decelerator (SIAD-R) was highly successful, and valuable data were collected during the test flight. This paper outlines the Computational Fluid Dynamics (CFD) analysis used to estimate the aerodynamic and aerothermal characteristics of the SIAD-R. Pre-flight and post-flight predictions are compared with the flight data, and a very good agreement in aerodynamic force and moment coefficients is observed between the CFD solutions and the reconstructed flight data.
Post-Flight Aerodynamic and Aerothermal Model Validation of a Supersonic Inflatable Aerodynamic Decelerator
2015
18 pages
Report
Keine Angabe
Englisch
Astronomy & Astrophysics , Extraterrestrial Exploration , Aerodynamics , Aerodynamic brakes , Aerodynamic coefficients , Thermal analysis , Models , Supersonic speed , Inflatable structures , Computational fluid dynamics , Computerized simulation , Geometry , Computational grids , Moment distribution , Force distribution , Deployment , Mach number , Hypervelocity wind tunnels , Proving , Heat flux
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