CHARACTERISTICS OF THE SHUTTLE ORBITER LEESIDE FLOW DURING A REENTRY CONDITION

A study of the leeside now characteristics of the Shuttle Orbiter is p resented for a re-entry night condition. The flow is computed using a point-implicit, finite-volume scheme known as the Langley aerothermody namic upwind relaxation algorithm (LAURA). LAURA is a second-order-acc urate, laminar Navier-Stokes solver incorporating finite-rate chemistr y with a radiative equilibrium wall temperature distribution and finit e-rate wall catalysis. The computational results are compared with mea sured inflight surface pressure and surface heating from several Shutt le Orbiter nights. In addition, a leeside surface temperature distribu tion is compared with a surface temperature distribution derived from the Shuttle infrared leeside temperature sensing (SILTS) flight experi ment.