A method of predicting boiling pressure drop for alkali metals.
Boiling pressure drop prediction for alkali metal bodies using correlation described by Stone and Damman
Stone, J. R.↗
SEARCH · Engineering Papers
Results for “prediction methods”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
A method of predicting heat transfer coefficients in the cooling passages of NERVA and Phoebus-2 rocket nozzles.
Heat transfer coefficients in rocket nozzle cooling passages predicted by equation developed from hydrogen flow experiments
Taylor, M. F.↗
A method for predicting interfacial freezing of a liquid flowing over a cold surface
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.
Savino, J. M.↗
An analysis of methods for predicting the stability characteristics of an elastic airplane. Appendix A - Equations of motion and stability criteria
Equations of motion and stability criteria for predicting stability and control characteristics of elastic aircraft
Source record↗
A method for predicting launch vehicle vibration levels in the region of the spacecraft adaptor
Prediction curves for launch vehicle vibration levels in region of spacecraft adaptor
Piersol, A. G.↗
Method for prediction of pump cavitation performance for various liquids, liquid temperatures, and rotative speeds
Prediction of cavitation performance of centrifugal pumps
Moore, R. D.↗
A method for predicting the performance of high reaction supersonic compressor blade sections.
Supersonic compressor blade sections performance prediction near maximum pressure ratio and efficiency by analyzing flow processes
Boxer, E.↗
A method for predicting pressures on elliptic cones at supersonic speeds
Two dimensional shock theory for predicting pressures on elliptic cones at supersonic speeds
Kaattari, G. E.↗
An approximate method for predicting pressure distributions on blunt bodies at angle of attack
Pressure distributions prediction on blunt bodies at angle of attack, considering bodies of revolution and large angle cones
Campbell, J. F.↗
An approximate method for predicting annulus inlet turbulent flow development characteristics
Newtonian fluid turbulent flow development characteristics in inlet region of smooth concentric annulus from momentum integral equations
Bathie, W. W.↗
An approximate method for predicting pressure distributions on blunt bodies at angle of attack
Pressure distributions prediction on blunt bodies at angle of attack, considering bodies of revolution and large angle cones
Campbell, J. F.↗
A method for predicting helicopter wake geometry, wake-induced flow and wake effects on blade airloads
Wake model and computer program to compute geometries, flows and velocity influence coefficients for helicopter blade load calculations
Sadler, S. G.↗
Development and application of a method for predicting rotor free wake positions and resulting rotor blade air loads. Volume 2: Program listings
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.
Sadler, S. G.↗
Development and application of a method for predicting rotor free wake positions and resulting rotor blade air loads. Volume 1: Model and results
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.
Sadler, S. G.↗
Method for predicting rotor free-wake positions and the resulting rotor blade airloads
Computer program has been designed and written to predict rotor free-wake positions and resulting rotor blade airloads without requiring time-consuming and tedious calculations. This program was written in FORTRAN IV for use on an IBM-360 computer.
Deen, D.↗
Method of predicting ionization-type vacuum gage sensitivity for various gases
Sensitivity of gage for one gas can be correlated to its sensitivity for other gases by the ratio of gas ionization cross sections. Ionization cross sections which best correlate with gage sensitivites vary according to gage type and ionization cross section energy level.
Holanda, R.↗
Analysis of flight test transition and turbulent heating data. Part 2: Turbulent heating results
The results of three turbulent heating predictions (Van Driest II, Spalding-Chi, and Walker Eckert reference enthalpy) have been compared to the data of several re-entry vehicles. Details and comparisons of each technique with the data are presented. The data analyzed cover a range of local Mach numbers of 3.3 to 15.2, wall to boundary layer edge temperature ratio of 0.46 to 2.6 and local Reynolds number of 7 times 10 to the 6th power to 5.3 times 10 to the 8th power. Data were transformed to an incompressible plane, using the prediction methods above, and compared with the Colburn and von Karman forms of the Reynolds analogy. The results indicate that the reference enthalpy technique best fits the data when the Colburn analogy was used; whereas, the Van Driest II method agrees with both forms of the Reynolds analogy. The Spalding-Chi method tends to under predict the data. Finally, there does not appear to be any significant difference when comparing the incompressible Stanton number as a function of Renolds number based on either wetted length or momentum thickness.
Laganelli, A. L.↗
A review of methods for predicting air pollution dispersion
Air pollution modeling, and problem areas in air pollution dispersion modeling were surveyed. Emission source inventory, meteorological data, and turbulent diffusion are discussed in terms of developing a dispersion model. Existing mathematical models of urban air pollution, and highway and airport models are discussed along with their limitations. Recommendations for improving modeling capabilities are included.
Mathis, J. J., Jr.↗