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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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Computer program for predicting silicon solar cell current-voltage characteristics as function of incident solar intensity and cell temperature over heliocentric distances
Relationship of shock standoff distance, at sonic and stagnation points, to body geometry of blunt bodies at zero angle of attack
Predicting heat transfer coefficients in cooling passages of Nerva and Phoebus-2 rocket nozzles
Computer program for calculating three dimensional magnetic field near magnetic bodies of field dependent permeability
Boiling pressure drop prediction for alkali metal bodies using correlation described by Stone and Damman
Heat transfer coefficients in rocket nozzle cooling passages predicted by equation developed from hydrogen flow experiments
Instantaneous thickness of a frozen layer is a function of specific heat, heat of fusion, temperatures, the frozen layer thickness at equilibrium, the thermal conductivity, and heat transfer coefficient. The equation can be evaluated on a desk calculator.
Equations of motion and stability criteria for predicting stability and control characteristics of elastic aircraft
Prediction curves for launch vehicle vibration levels in region of spacecraft adaptor
Prediction of cavitation performance of centrifugal pumps
Supersonic compressor blade sections performance prediction near maximum pressure ratio and efficiency by analyzing flow processes
Two dimensional shock theory for predicting pressures on elliptic cones at supersonic speeds
Pressure distributions prediction on blunt bodies at angle of attack, considering bodies of revolution and large angle cones
Newtonian fluid turbulent flow development characteristics in inlet region of smooth concentric annulus from momentum integral equations
Pressure distributions prediction on blunt bodies at angle of attack, considering bodies of revolution and large angle cones
Wake model and computer program to compute geometries, flows and velocity influence coefficients for helicopter blade load calculations
Computer program listings are presented for two separate programs: the wake geometry 1 blade loads and response. These listings correspond to the calculations discussed previously.
Rotor wake geometries are predicted by a process similar to the startup of a rotor in a free stream. An array of discrete trailing and shed vortices is generated with vortex strengths corresponding to stepwise radial and azimuthal blade circulations. The array of shed and trailing vortices is limited to an arbitrary number of azimuthal steps behind each blade. The remainder of the wake model of each blade is an arbitrary number of trailing vortices. Vortex element end points were allowed to be transported by the resultant velocity of the free stream and vortex-induced velocities. Wake geometry, wake flow, and wake-induced velocity influence coefficients are generated by this program for use in the blade loads portion of the calculations. Blade loads computations include the effects of nonuniform inflow due to a free wake, nonlinear airfoil characteristics, and response of flexible blades to the applied loads. Computed wake flows and blade loads are compared with experimentally measured data. Predicted blade loads, response and shears and moments are obtained for a model rotor system having two independent rotors. The effects of advance ratio, vertical separation of rotors, different blade radius ratios, and different azimuthal spacing of the blades of one rotor with respect to the other are investigated.