Afterbody heating characteristics of a proposed Mars Sample Return orbiter

Abstract

Abstract

Laminar-Turbulent Transition on Reentry Capsules and Planetary Probes

“…Horvath et al provide an equally good discussion of aeroheating to the afterbodies [19,20]. A shear layer separates from the edge of the blunt face, but can reattach to the afterbody depending on geometry.…”

“…Figure 9 shows that similar reattachment occurred with a smooth front face in another test at M 1 5:3 and a high Re D 3:3 10 6 , again suggesting an effect of transition on the front face ( [23], p. 9). [14] and cover of [19]. Fig.…”

“…Although moderate levels of lift can much improve the safety and flexibility of entry trajectories ( [2], Chap. 6), the Apollo geometry is proven in the very high aeroheating of a moon-return entry {11 km=s ( [3], p. 19)}, and easier to integrate with a launchescape rocket. The same CEV reentry geometry is to be used for both the low-energy entries from low earth orbit (LEO) and the very different high-energy entries from hyperbolic lunar and interplanetary missions.…”

Chapter 11: Heat Transfer and Flow Structure near the Planetary Probe Surface

“…2. MSRO [4] designed for delivering Martian soil samples to the Earth. It has an asymmetric shape because it is designed for entering the Martian atmosphere at an angle of attack: the frontal surface is inclined with respect to the free-stream direction, and the cylindrical payload container is parallel to this direction; the cylinder diameter is half the frontal shield diameter.…”

Comparison of a 3-D CFD-DSMC Solution Methodology With a Wind Tunnel Experiment

“…The MSRO configuration was experimentally studied [12] in the NASA Langley Research Center 20-Inch Mach 6 CF 4 Tunnel [13]. Hypersonic measurements of afterbody heating were performed in tetraflouromethane (CF4) test gas because it provides high density ratios across strong shock waves, which simulates hypersonic reacting gas flow conditions in flight.…”