An experimental investigation of some heat transfer characteristics on an orbiter/HO-tank/SRM Space Shuttle configurations, freestream Mach number equal to 8.0.
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Parker, J. Y.↗
Engineering topics
Barnett, D. O.
Publications and source records attributed to Barnett, D. O..
Shockwave-boundary layer interference heating analysis.
Interference heating correlations have been developed based on existing wind tunnel test data taken with simple configurations such as wedge/flat plate and compression corner models. For turbulent flow, peak interference heating was first correlated with shock strength (pressure ratio across shock wave) and then as a function of Reynolds number. The peak interference Stanton number was found to exhibit the same Reynolds number and Prandtl number characteristics as the Stanton number variation for undisturbed flow over a flat plate. Similar correlations were developed for laminar flow. Results indicated that for laminar flow at higher Reynolds number, the impinging shockwave may act as a boundary layer trip and cause boundary layer transition resulting in high interference heating. The correlations derived in this study can be used to scale wind tunnel model test data to a full-scale space vehicle at supersonic or hypersonic flight conditions.
Hung, F. T.↗
Acoustic loads at the base of engine clusters
Schlieren photography for acoustic loads at base of engine clusters
Barnett, D. O.↗
Plume characteristics of the Saturn cluster model
Pitot pressure distributions of jets measured in order to determine plume characteristics of Saturn cluster model
Barnett, D. O.↗
An investigation of liquid-hydrogen stratification in a large cylindrical tank of the saturn configuration.
Liquid hydrogen stratification test data for large cylindrical tank of Saturn configuration, using hyperbolic temperature profile and boundary layer considerations in analysis
TEMPERATURE GRADIENT↗
Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5
The effect of an external boundary layer on the performance of an axisymmetric external-internal-compression inlet was evaluated at Mach numbers of 3.0 and 2.5 and Reynolds numbers from 2.2 to 0.5 x 10(exp 6) per foot. The inlet was tested at locations up to two-thirds of the way into the 1.7- and 9.0-inch boundary layers generated by a flat plate and the tunnel floor, respectively. The inlet could be readily started at all conditions tested, including those where the boundary layer was separated upstream of the inlet by the various shock systems during the restart cycle. Although the inlet performance decreased with increasing immersion into the boundary layer at both Mach numbers, the inlet was more sensitive to boundary-layer ingestion at the design Mach number of 3.0.
Samanich, N. E.↗