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Roberts, B. B.

Publications and source records attributed to Roberts, B. B..

22 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

An exact solution of a simplified two-phase plume model

An exact solution of a simplified two-phase, gas-particle, rocket exhaust plume model is presented. It may be used to make the upper-bound estimation of the heat flux and pressure loads due to particle impingement on the objects existing in the rocket exhaust plume. By including the correction factors to be determined experimentally, the present technique will provide realistic data concerning the heat and aerodynamic loads on these objects for design purposes. Excellent agreement in trend between the best available computer solution and the present exact solution is shown.

Wang, S.-Y.↗
NASA NTRS1972

Reentry heating and flow fields for Space Shuttle Orbiter at high angle of attack.

Rarefied flow fields and heating rates are calculated by a Monte Carlo direct simulation technique for several shuttle orbiter configurations at angles of attack between 40 and 60 deg. Continuum inviscid flow fields are determined by 2-D unsteady and 3-D steady finite-difference/artificial viscosity techniques used in combination with a 2-D shock layer analysis method. Continuum viscous flow fields and heating rates are computed by a boundary-layer integral matrix technique and an aerodynamic heating method.

Rochelle, W. C.↗
NASA NTRS1972

Space shuttle orbiter reentry flow field and heating analysis

The reentry flow field and thermal environment around the straight wing shuttle orbiter vehicle were determined. Both rarefied and continuum flow fields and associated heating rates on various configurations representative of the orbiter at high angle of attack were calculated. Rarefied flow fields and heating rates were computed by the Monte Carlo direct simulation technique for altitudes above 82.3 km. Continuum inviscid flow fields were calculated by 2-D unsteady and 3-D steady finite difference/artificial viscosity methods and also by a 2-D shock layer analysis technique. Viscous flow fields and heating rates in the continuum regime were computed by a boundary layer integral matrix method for laminar flow and by an aerodynamic surface heating technique for turbulent flow. Shapes considered in the study included flat plates (representing the underside of the orbiter fuselage or the wing MAC), orbiter fuselage cross sections, orbiter wing airfoils, and 3-D orbiter configurations, all at high angle of attack (40 - 60 deg). The theoretical results showed good agreement with measured pressure and heat transfer data.

Rochelle, W. C.↗