Publication Date:
2019-07-13
Description:
Recently a very large (739 runs) collection of high-fidelity RANS CFD solutions was obtained for Space Launch System ascent aerodynamics for the vehicle to be used for the first exploratory (unmanned) mission (EM-1). The extensive computations, at full-scale conditions, were originally developed to obtain detailed line and protuberance loads and surface pressures for venting analyses. The line loads were eventually integrated for comparison of the resulting forces and moments to the database that was derived from wind tunnel tests conducted at sub-scale conditions. The comparisons presented herein cover the ranges 0.5 〈 or = M(infinity) 〈 or = 5, 6deg 〈 or = alpha 〈 or = 6deg, and 6deg 〈 or = beta 〈 or = 6deg. For detailed comparisons, slender-body-theory-based component build-up aero models from missile aerodynamics are used. The differences in the model fit coefficients are shown to be relatively small except for the low supersonic Mach number range, 1.1 〈 or = M(infinity) 〈 or = 2.0. The analysis is intended to support process improvement and development of uncertainty models.
Keywords:
Launch Vehicles and Launch Operations; Aerodynamics
Type:
NF1676L-22948
,
AIAA SciTech Forum 2016; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; Algeria
Format:
application/pdf
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