Abstract
Flowfield solutions over the Beagle 2 Mars probe aeroshell, spanning the trajectory through the Martian atmosphere, have been generated for the continuum flow regime for Mach numbers from 1.5 to 28 at angles of attack from 0 to 11 deg. Static aerodynamic coefficients C A , C N , and C m were derived from flow solutions generated by computational fluid dynamics (CFD) analysis. CFD derived data were applied, together with scaled existing data and wind tunnel experiments, to develop a static aerodynamic database applied in the entry and descent predictions for the Beagle 2 development program.
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