Comparisons of experimental and theoretical aerodynamic heating results in air-carbon dioxide mixtures
Convective aerodynamic heating estimates for air- carbon dioxide gas mixtures
CARBON DIOXIDE↗
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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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Comparison of experimental and kinetically limited theoretical performance of the hydrogen-fluorine propellant system
Theoretical calculations of hydrogen-fluorine rocket engine performance
ROCKET ENGINE↗
Comparison of experimental and theoretical shock shapes and pressure distributions on flat-faced cylinders at Mach 10.5
Integer relations method of determining inviscid shock layer flow and pressure distributions over blunt bodies
Inouye, M.↗
Comparison of experimental and predicted heat transfer characteristics for a cylindrical ejector
Heat transfer characteristics of cylindrical ejector for turbojet engine and shroud material temperature prediction
Chenoweth, F. C.↗
A comparison of experimental and calculated helium requirements for the pressurization of a Centaur liquid hydrogen tank
Ramp pressurization tests with gaseous helium in thick walled liquid hydrogen tank
Lacovic, R.↗
Experimental signal/noise-ratio comparison of the second-order phase-locked loop and the second-order frequency-locked loop.
Signal/noise performance of frequency locked loop FM threshold extension demodulator compared to phase locked loop demodulator and conventional FM discriminator
Schulman, R. J.↗
Calculation of nonequilibrium hypersonic turbulent boundary layers and comparisons with experimental data.
Compressible hypersonic turbulent boundary layers solution by finite difference method, relating mixing length to velocity profile shape factor
Beckwith, I. E.↗
Comparison of experimental and ideal leakage flows through labyrinth seals for very small pressure differences
Variable pressure leakage flow rate analysis on labyrinth seals
Cochran, R. P.↗
Comparisons of experimental and calculated electron transmission and bremsstrahlung spectra for electron energies below 3.0 MeV Final report, 12 Mar. 1969 - 12 Mar. 1970
Monte Carlo program for comparing thick-target bremsstrahlung and electron diffusion spectra
Rester, D. H.↗
Comparison of experimental and calculated helium requirements for pressurization of a Centaur liquid oxygen tank
Helium requirements for pressurization of Centaur liquid oxygen tank
Lacovic, R. F.↗
Numerical Solution of the Compressible Laminar, Transitional, and Turbulent Boundary Layer Equations with Comparisons to Experimental Data
Numerical solution of compressible laminar, transitional, and turbulent boundary layer equations
Harris, J. E.↗
Comparison of experimental and calculated critical masses for a gas core cavity reactor
Critical mass calculations for gas core cavity reactors
Gumto, K. H.↗
Comparison of experimental and analytical results for a 20-MW combustion-driven Hall configuration MHD generator
Combustion driven Hall configuration MHD generator, discussing boundary layer analysis, gas density nonuniformity and electrode drop
Brogan, T. R.↗
Calculation of nonequilibrium hypersonic turbulent boundary layers and comparisons with experimental data
Compressible hypersonic turbulent boundary layers solution by finite difference method, relating mixing length to velocity profile shape factor
Beckwith, I. E.↗
Calculation of electron concentration for a blunt body at orbital speeds and comparison with experimental data
Calculation of electron concentration for blunt nose at orbital speeds by use of pure air nonequilibrium chemistry throughout flow field and for same flow field with alkali contaminants
Evans, J. S.↗
Numerical solution of the equations for compressible laminar, transitional, and turbulent boundary layers and comparisons with experimental data
Numerical solution of flow equations for laminar, transitional, and turbulent compressible boundary layers for planar or axisymmetric flows
Harris, J. E.↗
Comparison of experimental and theoretical thermal fatigue lives for five nickel base alloys
The alloys Nimonic 90, IN 100, coated IN 100, B 1900, coated B 1900, MAR M200, and MAR M200DS (directionally solidified) were studied. Maximum temperatures ranged from 770 C to 1120 C (1420 F to 2050 F). Specimen geometries included tapered disks, double-edged wedges, and cambered airfoils. The disks and wedges were heated and cooled in fluidized beds. The airfoil specimens were heated by a Mach 1 natural gas burner and rapid-air-cooled, with and without spanwise loading. Life calculations included two distinct failure modes: conventional low cycle fatigue and cyclic creep. Required material properties were limited to conventional thermal, tensile, and creep rupture data. The complete life calculation system included the calculation of transient temperature distributions, thermal strains, stresses, creep damage, fatigue damage, and cycles to first crack. Calculated lives were within a factor of two for 76 of the 86 data points analyzed. Cyclic creep accounted for 81% of all the calculated damage.
Spera, D. A.↗
A program for calculating expansion-tube flow quantities for real-gas mixtures and comparison with experimental results
A computer program written in FORTRAN 4 language is presented which determines expansion-tube flow quantities for real test gases CO2 N2, O2, Ar, He, and H2, or mixtures of these gases, in thermochemical equilibrium. The effects of dissociation and first and second ionization are included. Flow quantities behind the incident shock into the quiescent test gas are determined from the pressure and temperature of the quiescent test gas in conjunction with: (1) incident-shock velocity, (2) static pressure immediately behind the incident shock, or (3) pressure and temperature of the driver gas (imperfect hydrogen or helium). The effect of the possible existence of a shock reflection at the secondary diaphragm of the expansion tube is included. Expansion-tube test-section flow conditions are obtained by performing an isentropic unsteady expansion from the conditions behind the incident shock or reflected shock to either the test-region velocity or the static pressure. Both a thermochemical-equilibrium expansion and a frozen expansion are included. Flow conditions immediately behind the bow shock of a model positioned at the test section are also determined. Results from the program are compared with preliminary experimental data obtained in the Langley 6-inch expansion tube.
Miller, C. G., III↗