Recent advances in research on compressible turbulent boundary layers
Review of prediction methods for compressible turbulent boundary layers
Beckwith, I. E.↗
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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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Prediction of the position and velocity of a satellite after many revolutions
Position and velocity prediction method for satellite after many revolutions
Dallas, S. S.↗
Bounds on epsilon-entropy with an l sub infinity error norm constraint
Geometric and predictive methods for developing bounds on epsilon-entropy for infinity error norm constraint
Davisson, L. D.↗
On the orientational transition in liquid crystals
Liquid crystals orientational ordering molecular field theory examined by cluster variation method, predicting first order transition
Etters, R. D.↗
Estimating carbon monoxide exposure
Method predicts effects of carbon monoxide on astronauts confined in spacecraft cabin atmospheres. Information on need for low toxicity level also applies to confined spaces. Benefits are applicable to industry and public health.
Edgerley, R. H.↗
Third Conference on Sonic Boom Research
Prediction methods for sonic boom generation and propagation with overpressure minimization in supersonic transport design and operation
Ira R. Schwartz↗
Panel and open conference discussions
Aircraft design and atmospheric turbulence effects on sonic boom generation and overpressure prediction methods using flight test data
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General remarks
Limitations of overpressure prediction methods for sonic boom configuration research
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Flow coefficients for supersonic nozzles with comparatively small radius of curvature throats
Small curvature radius/throat radius ratio supersonic nozzles mass flow rate coefficients at high Reynolds numbers, appraising isentropic flow prediction methods
Back, L. H.↗
Analysis of Free-Flight Laminar, Transitional, and Turbulent Heat-Transfer Results at Free-Stream Mach Numbers Near 20 (Reentry F)
Laminar, transitional, and turbulent heat-transfer data were measured during a reentry flight at a Mach number of 20 on a 5 deg half-angle cone 3.962 m (13 ft) long with an initial nose tip radius of 0.254 cm (0.1 in.). The free-stream Reynolds number increased during the prime data period from 7.0 x 10(exp 6) to 51.5 x 10(exp 6) per meter (2.1 x 10(exp 6) to 15.7 x 10(exp 6) per foot) and the ratio of wall to total temperature varied from 0.053 to 0.12. The angle of attack was less than 1deg for the prime data period. The experimental laminar and turbulent heating rates are compared with results from existing flat-plate prediction methods. At conditions of minimal tip blunting and angle of attack (above 26.8 km (88 000 ft)), values from a flat-plate laminar method agreed within 20 percent with the laminar data. The Schultz-Grunow skin-friction equation with reference enthalpy; conditions, with the Reynolds number based on distance from the transition location, and with the Colburn Reynolds analogy agreed within 10 percent with the experimental turbuleiit heating data. The Van Driest n skin-friction equation with Reynolds number greater than 10(exp 7) based on distance from the peak heating point and the Colburn Reynolds analogy was also within approximately 10 percent of the experimental turbulent heating data. A data correlation jbf the extent of transition and a simple empirical transition-zone heating correlation were also presented.
Zoby, Ernest V.↗
Plume backscatter measurements using quartz crystal microbalances in JPL Molsink (molecular sink)
Quantitative evidence of gas flows in the far upstream region of small nozzles with large boundary layer flow are discussed. Gas mass fluxes were measured using quartz crystal microbalances. Both nitrogen and carbon dioxide gases were used as test gases. Gas deposition rates on the order of 100 monolayers per minute were detected 13 inches upstream of the nozzle exit plane. It is significant to note that the crystals detected gases considerably beyond the Prandtl-Meyer turning angle. The data from these tests will be essential in the formulation of scaling laws and analytical prediction methods for viscous plume behavior.
Simon, W.↗
An experimental study of the hypersonic aerodynamics of delta wings.
Results of aerodynamic balance and pressure measurements carried out in a hypersonic gun tunnel (at a free-stream Mach number of 8.2 and a Reynolds number of 800,000) on delta wings having sharp leading edges swept at 70 and 76 deg. The experimental force and pressure coefficients and shock angles are discussed in relation to simple prediction methods. Some transition data are also included.
Rao, D. M.↗
Measurements of skin friction on the wall of a hypersonic nozzle.
Direct skin friction measurements obtained on the wall of a Mach 19.8 nozzle are presented. These measurements of skin friction and values deduced from the profile data are compared with predictions from a finite difference theory and also with several 'flat-plate' prediction methods for skin friction.
Harvey, W. D.↗
Optimization of a two stage light gas gun
Performance characteristics of the Texas A&M University light gas gun are presented along with a review of basic gun theory and popular prediction methods. A computer routine based on the simple isentropic compression method is discussed. Results from over 60 test shots are given which demonstrate an increase in gun muzzle velocity from 9.100 ft/sec. to 19,000 ft/sec. The data gathered indicated the Texas A&M light gas gun more closely resembles an isentropic compression gun rather than a shock compression gun.
Rynearson, R. J.↗
Applications of remote sensing to stream discharge predictions
A feasibility study has been initiated on the use of remote earth observations for augmenting stream discharge prediction for the design and/or operation of major reservoir systems, pumping systems and irrigation systems. The near-term objectives are the interpolation of sparsely instrumented precipitation surveillance networks and the direct measurement of water loss by evaporation. The first steps of the study covered a survey of existing reservoir systems, stream discharge prediction methods, gage networks and the development of a self-adaptive variation of the Kentucky Watershed model, SNOPSET, that includes snowmelt. As a result of these studies, a special three channel scanner is being built for a small aircraft, which should provide snow, temperature and water vapor maps for the spatial and temporal interpolation of stream gages.
Krause, F. R.↗
Life prediction of turbine components: On-going studies at the NASA Lewis Research Center
An overview is presented of the many studies at NASA-Lewis that form the turbine component life prediction program. This program has three phases: (1) development of life prediction methods for major failure modes through materials studies, (2) evaluation and improvement of these methods through a variety of burner rig studies on simulated components in research engines and advanced rigs. These three phases form a cooperative, interdisciplinary program. A bibliography of Lewis publications on fatigue, oxidation and coatings, and turbine engine alloys is included.
Spera, D. A.↗
High frequency fatigue testing of Udimet 700 at 1400 F
An investigation pertaining to the development of life prediction methods for materials subjected to high temperature creep/fatigue conditions is presented. High frequency (13.4 kHz) fatigue data were measured at 1400 F on specimens of the nickel-based alloy Udimet 700. Tests were conducted on the virgin material, as well as on specimens which had received prior exposures to high temperature, fatigue, and creep.
Conn, A. F.↗
Models of earth's atmosphere (90 to 2500 km)
This monograph replaces a monograph on the upper atmosphere which was a computerized version of Jacchia's model. The current model has a range from 90 to 2500 km. In addition to the computerized model, a quick-look prediction method is given that may be used to estimate the density for any time and spatial location without using a computer.
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