Analysis of two-phase impingement from a cryogen vented in orbit
Impingement pressure analysis associated with two phase cryogenic propellant venting to space environment
Evans, E. A.↗
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Results for “IMPINGEMENT”
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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An evaluation of rocket plume impingement effects on the Manned Orbital Workshop
High altitude scale model experiment to evaluate rocket plume impingement effects on Manned Orbital Workshop pressures, heating rates, forces and moments
Andrews, D.↗
Instability of a mechanical system induced by an impinging fluid jet
Critical load and instability of smooth and mesh surface mechanical systems subjected to impinging fluid jet, noting static buckling and flutter effects
Feldt, W. T.↗
Particle cloud impingement damage
Single impact data considered ineffective in estimating target damage induced by micron-sized particle cloud impingement
Laderman, A. J.↗
Noise from underexpanded axisymmetric jet flows using radial jet flow impingement
Acoustic radiation from underexpanded supersonic main jet flow from nozzle impinged upon by annular jet
Dosanjh, D. S.↗
Effect of orifice length-to-diameter ratio on mixing in the spray from a pair of unlike impinging jets
Orifice length-to-diameter ratio effect on spray mixture uniformity from unlike impinging jets
Riebling, R. W.↗
Forces due to air and helium jets impinging normal to a flat plate for near-vacuum and sea-level ambient pressures
Loads due to air and helium jets impinging normal to flat plate for near vacuum and sea level ambient pressures
Hoffman, S.↗
Combustion stability limits for swirl jet combustor modules combining air swirl and impinging jet atomization of ASTM A-1 fuel
Combustion stability limits for swirl-jet combustor modules combining air swirl and impinging jet atomization of ASTM A-1 fuel
Ingebo, R. D.↗
Space shuttle vehicle rocket plume impingement study for separation analysis Final report
Space shuttle vehicle rocket plume impingement study for separation analyses
Penny, M. M.↗
Apparatus for determining the deflection of an electron beam impinging on a target Patent
Apparatus to determine electric field strength by measuring deflection of electron beam impinging on target
Shriver, E. L.↗
Gas jet impingement normal to a liquid surface
Characteristics of gaseous jet impinging normally on liquid surface in regions where both gravitational and surface tension forces are significant
Aydelott, J. C.↗
Plume impingement during separation of a two stage space shuttle vehicle
Optimum separation trajectory analysis for two stage space shuttle configuration considering plume impingement effect
Fossler, I.↗
Combustion process of impinging hypergolic propellants
Combustor pressure poppings, stream mixing, and stream separation associated with combustion of impinging hypergolic propellants
White, J. R.↗
The effects of water impinging on thermally controlled surfaces under space conditions
Analysis of monochromatic reflectance changes due to impinging water spray from sharp-edge nozzles on thermally-controlled paints under space conditions
Maples, D.↗
Experimental investigation of leading-edge shock impingement and interaction heating on a 1/80 scale model of a NASA straight wing orbiter configuration at Mach numbers 8 and 16
Leading edge shock impingement and interaction heating on scale model straight wing orbiter
Rogers, C. E.↗
Comparison of temperature data from a four-vane static cascade and a research gas turbine engine for a chordwise-finned, impingement- and film-cooled vane
Experimental heat-transfer data obtained for a chordwise-finned, impingement- and film-cooled turbine vane tested in a four-vane static cascade to a gas temperature and a gas pressure of 2250 F and 80 psia, respectively, are presented. Average and local vane temperatures are correlated and compared with correlations of temperature data obtained from tests of the same vane in a modified J-75 turbojet engine. The measured vane temperatures obtained from these tests in the two test stands are also compared with analytically determined temperatures.
Gladden, H. J.↗
Design of a TF34 turbofan mixer for reduction of flap impingement noise
This portion of the TF-34 turbofan quiet engine studies has been devoted to the selection and design of a special mixer exhaust nozzle system to reduce the maximum 150 m (500 foot) sideline noise generated by the impingement of four engine exhausts on a STOL wing flap system to less than 92 PNdB. The design concept selected consists of a 12-lobe internal mixer and a 12-lobe external mixer mounted in series. The internal mixer reduces maximum exhaust velocities by mixing the fan and turbine streams. The external mixer is designed to reduce the velocity of the exhaust stream striking the wing flap surfaces. A ground test version of this concept has been designed to be installed and tested on an acoustically treated TF-34 engine nacelle, with flexibility to simulate a flight version of this concept which has also been defined. Estimated noise levels are 2 PNdB below the objective at approach and 2 PNdB above the objective at takeoff, with an uncertainty band of +3, -2 PNdB.
Chamay, A.↗
Comparison of heat-transfer test data for a chordwise-finned, impingement-cooled turbine vane tested in a four-vane cascade and a research engine
The heat-transfer characteristics of a chordwise-finned, impingement-cooled vane were investigated in both a modified J-57 research engine and a four-vane cascade. The data were compared by a correlation of temperature difference ratio with coolant- to gas-flow ratio and also by two modifications of this correlation. The results indicated that the cascade vane temperature data can generally be used to represent the engine vane temperature data. A discussion of engine and cascade gas-side heat-transfer coefficients is also presented. A redesign of the vane leading edge could significantly increase the potential turbine-inlet temperature operating limit.
Gladden, H. J.↗