Computations of Viking Lander Capsule Hypersonic Aerodynamics with Comparisons to Ground and Flight Data

摘要: Comparisons are made between the LAURA Navier-Stokes code and Viking Lander Capsule hypersonic aerodynamics data from ground flight measurements. Wind tunnel available for a 3.48 percent scale model at Mach 6 2.75 10.35, both under perfect gas air conditions. 1 also exist on-board instrumentation velocities 2900 4400 m/sec (Mach 14 to 23.3). flowfield solutions obtained geometry as tested or flown, including sting effects conditions finite-rate chemistry in flight. Using vehicle center-of-gravity location (trim angle approx. equals -11.1 deg), computed trim is within 0.31 degrees of derived 0.13 10.35 angle. lift drag force coefficients 2 measured data, lift-to-drag ratio 4 data. Computed 5 3 percent, respectively, wind nominal density profile location, 0.5 total instrumentation. 7 sensitivities atmospheric density, grid refinement generally small. The results will enable better estimate uncertainties future Mars entry vehicles where non-zero angle-of-attack required.