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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Compressible turbulent accelerating boundary layer flow model for convective heat transfer from rocket combustion gases, noting heat flux
DOWNSTREAM HEAT TRANSFER OF UPSTREAM MASS INJECTION IN SUPERSONIC LAMINAR BOUNDARY LAYER FLOW
Downstream heat transfer of upstream mass injectio in supersonic laminar boundary layer flow
Boundary layer flow in thin shock layer about axisymmetric blunt bodies studied by Blasius type series expansion technique
Compressibility transformation properties and high speed turbulent boundary layer flow with mass transfer and arbitrary pressure gradient
Gravity effect on conical vortex separator, predicting body force effect on heavy fluid boundary layer flow for limiting condition determination
Numerical analysis of shock induced boundary layer flow on semi-infinite flat plate - Part 2
Arc heated duct facilities providing high temperature supersonic turbulent boundary layer flows over large samples for orbital logistic vehicle thermal protection tests
Gortler instability of laminar boundary layer flow on concave wall with finite length effect for perturbation vortices
Electron density and temperature distribution in boundary layer flow of reflected shock tunnel conical nozzle
Velocity and temperature profiles at near-critical point of nitrogen turbulent boundary layer flow over heated flat plate by thermocouple/pitot- static probe
The overall problem of boundary layer flow transition is reviewed. Evidence indicates a need for new, basic physical hypotheses in classical fluid mechanics math models based on the Navier-Stokes equations. The Navier-Stokes equations are challenged as inadequate for the investigation of fluid transition, since they are based on several assumptions which should be expected to alter significantly the stability characteristics of the resulting math model. Strong prima facie evidence is presented to this effect.
Molecular sink facility and 25-foot space simulator have been used to distinguish nature of exhaust plumes from nozzles with relatively large internal boundary layer flow. Plume density has been measured by electron beam/photomultiplier system.
The effects of stall on a rotor blade element in a three-dimensional rotating environment was investigated. The model rotor test provided blade element airloads and local boundary layer flow characteristics at the three-quarter blade radius position for a wide range of rotor operating conditions. A description of the test program and the test results are presented.
A basis is provided for examining the stability of so-called 'shooting methods' and to examine the stability of the method successfully applied by Nachtsheim and Green (1970) to boundary-layer flow with large injection and heat transfer. The stability of that method is examined and confirmed.
Heat transfer data measured in gaps typical of those under consideration for joints in space shuttle reusable surface insulation protection systems have been assimilated, analyzed and correlated. The data were obtained in four NASA facilities. Several types of gaps were investigated with emphasis on simple butt joints. Gap widths ranged from 0.07 to 0.7 cm and depths ranged from 1 to 6 cm. Laminar, transitional and turbulent boundary layer flows over the gap opening were investigated. Three-dimensional heating variations were observed within gaps in the absence of external flow pressure gradients. Heat transfer correlation equations were obtained for several of the tests. Thermal protection system performance with and without gaps was compared for a representative shuttle entry trajectory.
It is shown that three-dimensional and time-dependent boundary layer flows can be calculated in a reasonable amount of time with the current generation of computers. The physical problems used to illustrate this have a wide application, and are the following: (1) oscillating flows over cylinders with both the wall and the inviscid flow oscillating, and (2) time-dependent and three-dimensional flow over a rotating airfoil in forward flight.
Weak shock-wave interactions with boundary layers on a flat plate were investigated experimentally in Mach 8 variable-density tunnel for plate-length Reynolds numbers. The undisturbed boundary layers were laminar over the entire plate length. Pressure and heat-transfer distributions were obtained for wedge-generated incident shock waves that resulted in pressure rises ranging from 1.36 to 4.46 (both nonseparated and separated boundary-layer flows). The resulting heat-transfer amplifications ranged from 1.45 to 14. The distributions followed established trends for nonseparated flows, for incipient separation, and for laminar free-interaction pressure rises. The experimental results corroborated established trends for the extent of the pressure rise and for certain peak heat-transfer correlations.