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At least 1,729 records · Page 96
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NASA NTRS1974

The application of holography to the visualization of shock patterns in a transonic compressor

This paper describes an experiment in the application of holographic interferometry to the visualization of flow in a transonic compressor. The principal objective of the study was to visualize the shock waves created by the rotor blades and to determine their relative orientation in three dimensions. The technique employed double-pulse, double-exposure holography to record the flow field through a plastic window built into the outer case over the rotor blades. Illumination was by diffuse reflection from the interior surfaces of the compressor. No other optical components in or on the compressor were used. The resulting holograms successfully showed the upstream bow shocks and, at high speed, the outer-most portion of the leading edge passage shock. Techniques were devised for locating these shocks in three dimensions and the results were compared with theoretical predictions. In all cases, the shock angles were somewhat larger than predicted by theory, and a distinct increase in angle near the outer wall was observed, which may be attributed to end wall boundary layer effects.

Hantman, R. G.↗
NASA NTRS1974

Radiation-gas dynamic shock layer coupling

The present work considers theoretically the problem of radiation losses on the shock layer during hypersonic flight, and in particular, results are presented for the stagnation line shock layer for a wide variety of flight conditions, providing a new overview of radiation-gas dynamic coupling within a shock layer. The present results are based on a previous model (Engel, Farmer, et al., 1973) of a viscous radiating shock layer. An important result is that the radiation-gas dynamic coupling effect on the radiative heating can be related to a single parameter, namely, the radiative cooling parameter, whereas the effect on the shock layer thickness is not a simple function of this parameter.

Engel, C. D.↗
NASA NTRS1975

Shock shapes on blunt bodies in hypersonic-hypervelocity helium, air, and CO2 flows, and calibration results in Langley 6-inch expansion tube

Shock shape results for flat-faced cylinders, spheres, and spherically blunted cones in various test gases, along with preliminary results from a calibration study performed in the Langley 6-inch expansion tube are presented. Free-stream velocities from 5 to 7 km/sec are generated at hypersonic conditions with helium, air, and CO2, resulting in normal shock density ratios from 4 to 19. Ideal-gas shock shape predictions, in which an effective ratio of specific heats is used as input, are compared with the measured results. The effect of model diameter is examined to provide insight to the thermochemical state of the flow in the shock layer. The regime for which equilibrium exists in the shock layer for the present air and CO2 test conditions is defined. Test core flow quality, test repeatability, and comparison of measured and predicted expansion-tube flow quantities are discussed.

Miller, C. G., III↗
NASA NTRS1975

Installation and airspeed effects on jet shock-associated noise

Experimental acoustic data are presented to illustrate, at model scale, the effect of varying the nozzle-wing installation on shock-associated noise, statically and with airspeed. The variation in installations included nozzle only, nozzle under-the-wing (with and without flaps deflected), and nozzle over-the-wing (unattached flow). The nozzles used were a conical and a 6-tube mixer nozzle with a cold-flow nozzle pressure ratio of 2.1. A 33-cm diameter free jet was used to simulate airspeed. With the nozzle only, shock wave noise dominated the spectra in the forward quadrant, while jet mixing noise dominated in the rearward quadrant. Similar trends were observed when a wing (flaps retracted) was included. Shock noise was attenuated with an over-the-wing configuration and increased with an under-the-wing configuration (due to reflection from the wing surface). With increasing flap deflection (under-the-wing configuration), the jet-flap interaction noise exceeded the shock noise and became dominant in both quadrants. The free jet results showed that airspeed had no effect on shock noise. The free jet noise data were corrected for convective amplification to approximate flight and comparisons between the various configurations are made.

Vonglahn, U.↗
NASA NTRS1974

Distant bow shock observations by Explorer 33

Locations, orientations and magnetic field changes are given for 135 bow shock crossings at distances downstream from earth between 84 and 117 earth radii. The shock locations bracket those calculated for the hypersonic analogue by Dryer and Heckman (1967) for a Mach number of 3.8. The shock normal vectors have been calculated using magnetic coplanarity. The average normal vectors have a greater inclination by about 17 plus or minus 5 deg from the symmetry axis than the Dryer and Heckman shock orientations for a 3.8 Mach number. Over a range of downstream distances from 60 to 115 earth radii, the median magnetic field magnitude jump across the shock changes from 1.90 to 1.70 times.

Mihalov, J. D.↗
NASA NTRS1975

Structure of the quasi-perpendicular laminar bow shock

It was found that low solar wind parameters M (less than or around 2.5) and beta (much less than 1) and high angles to the local shock normal, theta (greater than or around 65 deg), produced oblique laminar shock profiles as expected from theory, with marginal or vanishing upstream standing whistlers probably damped by acoustic or other plasma wave instabilities. The whistler mode appeared to dominate the electromagnetic spectrum. The laminar shock ramp thickness was several hundred kilometers and equal to (2-4)c/omega-pi. Composition of the shock as an accumulation of near-standing waves and an evidently reproducible varying flux pattern was discernible. Electron thermalization occurred early in, or just before, the magnetic ramp, while proton thermalization appeared to occur later in the ramp. Instantaneous shock velocities derived from the standing whistler wavelength were consistent with average velocities derived from the elapsed time estimates and were as high as 200 km/sec.

Greenstadt, E. W.↗
NASA NTRS1975

Standing waves at low Mach number laminar bow shocks

Explorer 43 data were used to study 34 bow shock crossings observed from 5 to 16 earth radii upstream of the average bow shock location. Waves with periods of 6 to 130 s having amplitudes up to delta-B/B = 1 were detected. Wave polarization for the low-frequency waves is right-handed in relation to the average field direction when the observer moves from the upstream to downstream direction but is left-handed when the observer moves in the opposite sense. This fact identified the waves as standing whistler waves in the coordinate system of the shock. The waves are in agreement with collisionless low Mach number laminar shock theory. When the measured parameters were used to calculate theoretical wavelengths, the observed wave frequencies could be used to calculate velocities for the shock-wave coordinate system past the spacecraft; such velocities are mostly between 10 and 30 km/s. It is suggested that the higher-frequency propagating whistler waves may evolve from the standing whistler waves through a decay instability.

Fairfield, D. H.↗
NASA NTRS1974

Shock-induced melting in anorthositic rock 60015 and a fragment of anorthositic breccia from the 'picking pot' /70052/

Microscopic and chemical evidence are presented to support the contention that shock-generated incipient grain-boundary melting of plagioclase occurred in an anorthositic lunar rock and that shock-generated plagioclase liquid was present along grain boundaries during post-shock adiabatic expansion in a fragment of anorthositic breccia. The first contention is supported by microtextural relationships in the rock, the composition of its metal particles (most iron with some cobalt and less nickel), and glass inclusions with vapor bubbles. The second contention is supported by angular irregular voids in the fragment as well as the occurrence of oriented glass filaments in some of the voids. It is shown that shock-generation of 'cataclastic anorthosite' and high-temperature plagioclase liquids can explain the exceptionally young lead and argon ages of the anorthositic rock. The results of the breccia study indicate that shock lithification of plagioclase-rich particulate material from the highland regolith is due to grain-boundary melting of plagioclase.

Sclar, C. B.↗
NASA NTRS1975

Pioneer 9 and OGO 5 observations of an interplanetary multiple shock ensemble on February 2, 1969

A multiple shock system was observed upstream (0.13 AU) of the earth by Pioneer 9 on February 2, 1969. The same system was observed at earth by Ogo 5 and was reported separately in the literature. This paper compares the two sets of observations in still further detail. Both magnetic-field and plasma data are used in a least-squares best-fit method to compute the characteristics of the fast forward shock wave (Pioneer 9 only) and two fast reverse shock waves. Nearly all major features (shock, piston, and tangential discontinuity) retained their characteristics during the transit of the shock ensemble from Pioneer 9 to Ogo 5. The genesis of the ensemble is believed to be due to a complex stream-stream interaction. A substantial density increase (including a large rise of alpha/proton abundance) at Ogo 5, but unobserved at Pioneer 9, is explained by a sudden meridional shift to a flow from below the ecliptic plane while the streams were en route to earth. This study demonstrates a spatial and temporal plasma inhomogeneity which is superimposed on the persistent major features.

Dryer, M.↗
NASA NTRS1975

The upstream escape of energized solar wind protons from the bow shock

The paper analyzes the geometry of escape from the bow shock for solar wind protons in order to determine under what conditions a proton reflected from the bow shock can escape upstream or not. Some numerical examples show that protons with rather high energies and pitch angles can escape the shock at only marginally quasi-parallel field orientations, even if they have quite moderate speeds parallel to B. This does not provide evidence that such high energy protons are produced at the bow shock, but does show that such protons can escape upstream with the characteristics observed by Lin et al. (1974). It is also possible that some particles will encounter the shock two or more times, their total energy compounding until it reaches a high level.-

Greenstadt, E. W.↗
NASA NTRS1975

A comparison of measured and predicted sphere shock shapes in hypersonic flows with density ratios from 4 to 19

Measured shock shapes are presented for sphere and hemisphere models in helium, air, CF4, C2F6, and CO2 test gases, corresponding to normal-shock density ratios (primary factor governing shock detachment distance of blunt bodies at hypersonic speeds) from 4 to 19. These shock shapes were obtained in three facilities capable of generating the high density ratios experienced during planetary entry at hypersonic conditions; namely, the 6-inch expansion tube, with hypersonic CF4 tunnel, and pilot CF4 Mach 6 tunnel (with CF4 replaced by C2F6). Measured results are compared with several inviscid perfect-gas shock shape predictions, in which an effective ratio of specific heats is used as input, and with real-gas predictions which include effects of a laminar viscous layer and thermochemical nonequilibrium.

Miller, C. G., III↗
NASA NTRS1975

Pyroxenes and olivines: Structural implications of shock-wave data for high pressure phases

The nature of the shock-induced, high-pressure phases of olivine and pyroxene rocks is examined in the light of data for the densities of a new class of perovskite-related silicate structures. Also examined are some new Hugoniot and release adiabat data for bronzite. Reexamining available shock data for magnesian pyroxenes and olivines leads to the conclusion that they define a mixed phase (or disequilibrium) region to about the 100 GPa range, related to the kinetics of phase transformation in these silicates. By recognizing this point, certain discrepancies in previous interpretations of shock data can be explained. A set of theoretical Hugonoits for pyroxene and olivine stoichiometry, perovskite-bearing assemblages was constructed based on their properties deduced from high-pressure work, showing that the shock data is compatible with transformations to perovskites in the 45-7GPa region. Finally, the shock data indicate very similar properties for olivine and pyroxene at high pressures making them both equally likely candidates for the lower mantle.

Jeanloz, R.↗
NASA NTRS1975

Installation and airspeed effects on jet shock-associated noise

Experimental acoustic data are presented to illustrate, at model scale, the effect of varying the nozzle-wing installation on shock-associated noise, statically and with airspeed. The variation in installations included nozzle only, nozzle under-the-wing, and nozzle over-the-wing. With the nozzle only, shock wave noise dominated the spectra in the forward quadrant, while jet mixing noise dominated in the rearward quadrant. Similar trends were observed when a wing (flaps retracted) was included. Shock noise was attenuated with an over-the-wing configuration and increased with an under-the-wing configuration (due to reflection from the wing surface). With increasing flap deflection (under-the-wing configuration), the jet-flap interaction noise exceeded the shock noise and became dominant in both quadrants. The free jet results showed that airspeed had no effect on shock noise.

Von Glahn, U.↗
NASA NTRS1975

Use of shock tubes in high Reynolds number transonic testing

The shock tube as a device to fulfill current needs for testing of transonic airfoils at high Reynolds numbers is considered. Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be produced. A study of flow development over a simple airfoil has been carried out in a shock tube at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photography and airfoil pressure measurements show that steady transonic flows similar to those produced for the same airfoil in a wind tunnel can be generated within the available testing time in a shock tube with properly contoured test section walls. The study indicates that the shock tube is a viable alternative as a facility for studying high Reynolds number transonic airfoil flows.

Cook, W. J.↗
NASA NTRS1976

Correlation of bow shock plasma wave turbulence with solar wind parameters

The rms field strengths of electrostatic and electromagnetic turbulence in the earth's bow shock, measured in the frequency range 20 Hz to 200 kHz with the Imp 6 satellite, are examined. The largest strengths of electrostatic turbulence occur when the upstream electron-to-proton temperature ratio is large and the proton temperature is small. No substantial correlation is found among the rms field strengths of electrostatic turbulence, the Alfven Mach number, the ratio of particle to magnetic-field pressure, and the shock normal angle. These results indicate that the strength of electrostatic turbulence in the bow shock is determined by the kinetic properties of the solar-wind plasma. The largest strengths for electromagnetic turbulence occur when the upstream particle density is large and when the shock normal angle is closer to 90 deg, supporting a previous conclusion that whistler waves comprise the electromagnetic turbulence in the bow shock.

Rodriguez, P.↗
NASA NTRS1976

A study of a plume induced separation shock wave, including effects of periodic plume unsteadiness

A wind tunnel investigation was conducted to study the flow field in which separation is caused by an expanding plume, with emphasis on effects associated with periodic unsteadiness in the plume. The separation shock was photographed with high speed motion pictures, from which mean shock position and excursion data were reported. Pressure fluctuations were measured beneath the separation shock. A response of the separation shock to plume periodic unsteadiness was identified, and the magnitude of a corresponding transfer function was defined. Small harmonic effects in plume response to periodic unsteadiness were noted. The stabilizing effect of a lateral surface protuberance near the separation shock wave was investigated. The protuberance configuration was a lateral circular cylinder, and various diameters, all less than the boundary layer thickness, were employed.

Doughty, J. O.↗
NASA NTRS1976

Flow and heat transfer measurements in a pseudo-shock region with surface cooling

An experimental investigation was conducted to acquire information on the flow structure, mean flowfield, and temperature distributions in a pseudo-shock region in a supersonic diffuser with surface cooling. The Mach number upstream was 2.9, and the wall to stagnation temperature ratio was 0.44. A Mach-disk-like shock wave emanated from the thin separated flow region near the beginning of the compression region, and reattachment occurred one diameter downstream so that the flow was not separated over most of the pseudo-shock region. The flow compression was a shock-free, predominantly viscous process. Along the pseudo-shock region the measured heat-transfer coefficient increased approximately as the 0.8 power of the measured wall static pressure. The estimated wall shear stress increased downstream of flow attachment, but was still considerably less than the upstream value.

Cuffel, R. F.↗
NASA NTRS1976

Three-dimensional aspects of interplanetary shock waves

The three-dimensional geometries of two classes of interplanetary shock waves are analyzed: (1) the more or less spherical shock wave originating from some short-lived solar event, such as a solar flare, and (2) the corotating shock pair formed by the interaction of long-lived solar wind streams. The systematic distortion of a spherical wave due to persistent latitudinal solar wind structure should amount to 25 deg for an equator-to-pole solar wind speed differential of 200 km/sec. A geometrical argument is given for determining the heliocentric distance of the onset of corotating shocks formed by contiguous long-lived solar streams. Estimates are obtained for the heliocentric distance to the inner edges of shock waves as a function of speed difference between the streams and as a function of heliographic latitude. Means by which the three-dimensional structures studied can be observed by out-of-the-ecliptic space missions are discussed.

Siscoe, G. L.↗