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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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At least 703 records · Page 39
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Photographing flow fields and heat-transfer patterns in color simultaneously.

A color-schlieren technique is described that combines the flow-field shock shapes and the phase-change coating to give a very descriptive account of aerodynamic heating. This technique employs, in addition to the conventional schlieren system, a temperature-sensitive material as a thin surface coating that undergoes a visible phase change from opaque solid to clear liquid at a known temperature. The resulting pictures can lead to a better understanding of shock/boundary layer interactions, as shown with the aid of a specific example.

Creel, T. R., Jr.↗
NASA NTRS1972

Laboratory simulation of diffuse reflectivity from a cloudy planetary atmosphere.

For the first time measurements in the multiple scattering regime of the diffuse reflectivity as a function of single scattering albedo have been made in a geometry that may be simulated by a plane parallel atmosphere of large optical depth. A comparison between the measurements and a theoretical computation of the diffuse reflectivity is presented. The measurements are within 1% agreement with the theoretical calculations for two different sizes of scattering particles which are larger than and smaller than the wavelength of the incident light, corresponding to the Mie and Rayleigh regimes, respectively.

Margolis, J. S.↗
NASA NTRS1972

Measurement and analysis of the nu3 band of methane.

The resolution enhancement procedure of Jansson et al. (1970) is applied to new high resolution spectra to obtain additional information about the tetrahedral fine structure. The effective vibration-rotation Hamiltonian given by Susskind (1972) is then used to interpret these data. It is found that virtually every detail of the observed spectrum is predicted. Many details of the deconvoluted spectra which were not evident in the observed spectrum are verified.

Barnes, W. L.↗
NASA NTRS1972

Formation of spectral lines in planetary atmospheres. III - The use of analytic scattering diagrams in computations of synthetic spectra for cloudy atmospheres.

Results of some comparisons that have been made of line profiles and equivalent widths computed from atmospheric models where the scattering has been represented by the Mie theory and a simple analytic expression, the Heyney-Greenstein function. These results show that the spectroscopic features for these models are indistinguishable and demonstrate the value of using this simple analytic function in terms of the great saving in computer time when computing synthetic spectra for any cloudy planetary atmosphere.

Hunt, G. E.↗
NASA NTRS1972

Venus cloud cover.

It is shown that the presence of a cloud free region on Venus is not necessary for explaining the upward and downward atmospheric motions suggested by Goody and Robinson (1966) in the Venusian atmosphere. Considerations are given in support of the assumption that the cloud cover on Venus may be solid.

Bartlett, J. T.↗
NASA NTRS1973

Heating and flow-field studies on a straight-wing hypersonic reentry vehicle at angles of attack from 20 to 80 deg with simulation of real-gas trends

Data are presented from a series of phase-change heat transfer and flow visualization tests at Mach 7.4, 8, and 10.3 in air, Mach 19.5 in nitrogen, Mach 20.3 in helium, and Mach 6 in tetrafluoromethane (CF4) on the windward surface of a straight wing hypersonic reentry configuration for angles of attack from 20 deg to 80 deg. The results indicate that: (1) for hypersonic stream Mach numbers, the flow field over the straight-wing configuration is essentially independent of Mach number, (2) transition Reynolds number decreases with increasing angle of attack, (3) at some critical angle of attack, the wing-shock standoff distance is greatly increased and the stagnation line moves downstream from the wing leading edge, (4) value of the critical angle of attack is very sensitive to the flow shock density ratio or effective gamma, and (5) at angles of attack above the critical value for all gases, the nondimensional level of heat transfer to the wing is higher for the higher shock density ratio flows.

Hunt, J. L.↗
NASA NTRS1973

Thermodynamic and transport properties of gaseous tetrafluoromethane in chemical equilibrium

Equations and in computer code are presented for the thermodynamic and transport properties of gaseous, undissociated tetrafluoromethane (CF4) in chemical equilibrium. The computer code calculates the thermodynamic and transport properties of CF4 when given any two of five thermodynamic variables (entropy, temperature, volume, pressure, and enthalpy). Equilibrium thermodynamic and transport property data are tabulated and pressure-enthalpy diagrams are presented.

Hunt, J. L.↗
NASA NTRS1973

Application of phase-change technique to thin sections with heating on both surfaces

A numerical digital computer program was developed to calculate the heat-transfer coefficients for both sides of a one-dimensional finite slab subject to the boundary conditions ascribed to the phase-change coating heat-transfer technique. In a typical tunnel test situation where a thin wing was exposed to heating on both sides, the data reduction procedures for a semi-infinite slab gave heat-transfer coefficients as much as 375 percent too high on the side with the lowest heating. The results from the one-dimensional finite-slab procedure are presented in the form of correction factors to the solution for a semi-infinite slab in terms of parameters normally used with the phase-change heat-transfer technique. These correlations are not restricted to slab thickness or thermophysical properties and are easily used to obtain accurate data on thin model sections.

Hunt, J. L.↗
NASA NTRS1973

Loading and heating of a large flat plate at Mach 7 in the Langley 8-foot high-temperature structures tunnel

Surface pressure and cold-wall heating rate distributions (wall-temperature to total-temperature ratio approximately 0.2) were obtained on a large, flat calibration panel at a nominal Mach number of 7 in an 8-foot high-temperature structures tunnel. Panel dimensions were 42.5 by 60.0 in. Test objectives were: (1) to map available flat-plate loading and heating provided by the facility and (2) to determine effectiveness of leading-edge bluntness, boundary-layer trips, and aerodynamic fences in generating a uniform, streamwise turbulent flow field over the test surface of a flat-sided panel holder.

Deveikis, W. D.↗
NASA NTRS1972

Line formation in a Jovian atmosphere.

The nominal model of the Jovian atmosphere proposed by Divine (1970) is used as a basis for an interpretation of spectroscopic observations. The results discussed are concerned with those observations which may be quantitatively interpreted, i.e., the R-branch of the 3 nu sub 3 band of methane centered at 1.1 micron, and the hydrogen quadrupole spectrum. The results give a self-consistent model for the structure and composition of the atmosphere, and the radiative properties of the visible cloud layers.

Hunt, G. E.↗
NASA NTRS1972

Informational biopolymer structure in early living forms.

Some studies devoted to the search in various organisms for 'relics' of the biochemical nature of ancient organisms, preserved by the conservative nature of the evolutionary process in all living species, are reviewed. Investigations of five families of informational molecules constituting such 'relics' in very diverse organisms are reported. They include: cytochrome c, ferredoxin, trypsin, transfer ribonucleic acid (RNA), and 5S ribosomal RNA. It is shown that, even from these few informational molecules, some interesting inferences about early living organisms can be drawn.

Dayhoff, M. O.↗
NASA NTRS1973

The many uses of the dirigible.

Prospects for a revival of large airships are based on a number of unique services which can be provided by the dirigibles. It is shown that airships are not unduly weather-sensitive. Modern technological advances will give the airship of the future operational features which will be greatly superior to those of the Zeppelins of the past. Projections set the payload of a 22-million-cu ft conventionally propelled airship of conservative design at 615,000 lb for a range of 2950 mi. The corresponding figure for the C-5A aircraft is only 265,000 lb. Dirigibles could, therefore, become merchant ships of the air, carrying low-density and large-dimension cargoes that jet freighters find economically unattractive or practically impossible to handle. The absence of landing-facility requirements would make the airship a logical candidate for introducing trade into otherwise inaccessible regions of the world.

Hunt, J. R.↗