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At least 937 records · Page 52

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NASA NTRS1973

Investigation of flow fields within large scale hypersonic inlet models

Analytical and experimental investigations were conducted to determine the internal flow characteristics in model passages representative of hypersonic inlets for use at Mach numbers to about 12. The passages were large enough to permit measurements to be made in both the core flow and boundary layers. The analytical techniques for designing the internal contours and predicting the internal flow-field development accounted for coupling between the boundary layers and inviscid flow fields by means of a displacement-thickness correction. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide high internal performance with an approximately uniform static-pressure distribution at the throat station. The models were tested in the Ames 3.5-Foot Hypersonic Wind Tunnel at a nominal free-stream Mach number of 7.4 and a unit free-stream Reynolds number of 8.86 X one million per meter.

Gnos, A. V.↗

NASA NTRS1973

Hypersonic flows in large-scale inlet models.

Analytical and experimental investigations were conducted to determine the characteristics of the internal flows in model passages representative of inlets for a typical Mach 12 hypersonic cruise vehicle and also sufficiently large for reliable data to be obtained. Three large-scale inlet models, each having a different internal compression ratio, were designed to provide maximum performance at the throat stations. Tests were conducted in the Mach 7.4 nozzle of the NASA Ames 3.5-foot hypersonic wind tunnel at a nominal test Reynolds number of 2,700,000 per ft. The experimental results revealed that a high level of total pressure recovery, approximately 0.85 (relative to the inlet-entrance conditions) for the core flow of the internal passage, was achieved for each inlet design.

Seebaugh, W. R.↗

NASA NTRS1974

Comparison of transition and freestream disturbance measurements obtained in two wind tunnel facilities

Boundary-layer transition measurements have been made on two 5-deg half-angle cones at Mach 7 in the Ames 3.5-foot and the Langley variable density wind tunnels. Although there were differences between the measured freestream disturbance scales and pressure fluctuation levels, the choice of consistent locations within the transition region, using either thin-film fluctuation or surface heat-transfer data results in excellent agreement between the transition Reynolds numbers in both facilities. However, there is an apparent connection between changes in freestream pressure fluctuation levels and movement of boundary-layer transition location in the two facilities.

Owen, F. K.↗

NASA NTRS1975

Waveguide CO2 laser gain: Dependence on gas kinetic and discharge properties

Using a simple rate equation approach the gas kinetic and discharge properties of waveguide CO2 lasers were examined. The dependence was calculated of the population inversion and laser small signal gain on gas pressure, gas mixture, pumping rate (discharge current), tube bore diameter, and wall temperature. At higher pressures the gain is optimized by using more helium rich mixtures and smaller bore diameters. The dependence of laser tunability on the gas kinetic properties and cavity losses was determined, it was found that for loss cavities the laser tunability may substantially exceed the molecular fullwidth at half maximum. The more helium rich gas mixtures give greater tunability when cavity losses are small and less tunability when cavity losses are large. The role of the various gases in the waveguide CO2 laser is the same as that in conventional devices, by contrast with conventional lasers, the waveguide laser transition is homogeneously broadened. The dependence of gain on gas pressure and other kinetic and discharge properties differs substantially from that predicted by scaling results from conventional low pressure lasers.

Cohen, S. C.↗

NASA NTRS1975

Flow visualization of vortex interactions in multiple vortex wakes behind aircraft

A flow visualization technique was developed which allows the nature of lift-generated wakes behind aircraft models to be investigated. The technique was applied to models being towed underwater in a ship model basin. Seven different configurations of a small-scale model of a 747 transport aircraft were used to allow observation of typical vortex interactions and merging in multiple vortex wakes. It was established that the motion of the wake vortices is often sensitive to small changes in either wing span loading or model attitude. Landing gear deployement was found to cause a far-field reformation of vorticity behind a model configuration which dissipated concentrated vorticity in the near-field wake. Alleviation of wake vorticity is achievable by configuring the wing span loading to cause the wake vortices to move in paths that result in their interactions and merging. The vortices shed from the horizontal stabilizer always moved down rapidly into the wake and merged with the other vortices, primarily the inboard flap vortices.

Ciffone, D. L.↗

NASA NTRS1976

Waveguide CO2 laser gain - Dependence on gas kinetic and discharge properties

A simple rate-equation approach is used to examine the gas-kinetic and discharge properties of waveguide CO2 lasers. The dependence of the population inversion and laser small-signal gain on gas pressure, gas mixture, pumping rate (discharge current), tube bore diameter, and wall temperature is calculated along with the dependence of laser tunability on the gas-kinetic properties and cavity losses. It is found that for low-loss cavities, the laser tunability may substantially exceed the molecular full width at half-maximum. Furthermore, the more helium-rich gas mixtures give greater tunability when cavity losses are small, and less tunability when cavity losses are large. By contrast with conventional lasers, the waveguide-laser transition is homogeneously broadened. Thus, the dependence of gain on gas pressure and other kinetic properties differs substantially from that predicted by scaling results from conventional low-pressure lasers.

Cohen, S. C.↗

NASA NTRS1976

Results of the plasma analyzer experiment on Pioneers 10 and 11

The plasma-analyzer experiments on Pioneers 10 and 11 have determined that the characteristics of the solar-wind interaction with the Jovian magnetosphere are basically similar to those observed for the solar-wind interaction of earth and differ mainly in terms of the scale size of the interaction. The Jovian magnetosheath flow field and the calculated normals to the Jovian magnetosphere indicate that the Jovian magnetosphere is extremely thick and blunt in shape. The size of the Jovian magnetosphere in the sunward (dayside) direction can change by as much as a factor of two in response to relatively minor changes in solar-wind dynamic pressure. The outer dayside Jovian magnetosphere is inflated with a high-beta thermal plasma.

Intriligator, D. S.↗

NASA NTRS1977

Noise characteristics of upper surface blown configurations. Experimental program and results

An experimental data base was developed from the model upper surface blowing (USB) propulsive lift system hardware. While the emphasis was on far field noise data, a considerable amount of relevant flow field data were also obtained. The data were derived from experiments in four different facilities resulting in: (1) small scale static flow field data; (2) small scale static noise data; (3) small scale simulated forward speed noise and load data; and (4) limited larger-scale static noise flow field and load data. All of the small scale tests used the same USB flap parts. Operational and geometrical variables covered in the test program included jet velocity, nozzle shape, nozzle area, nozzle impingement angle, nozzle vertical and horizontal location, flap length, flap deflection angle, and flap radius of curvature.

Brown, W. H.↗

NASA NTRS1981

Numerical solutions of atmospheric flow over semielliptical simulated hills

Atmospheric motion over obstacles on plane surfaces to compute simulated wind fields over terrain features was studied. Semielliptical, two dimensional geometry and numerical simulation of flow over rectangular geometries is also discussed. The partial differential equations for the vorticity, stream function, turbulence kinetic energy, and turbulence length scale were solved by a finite difference technique. The mechanism of flow separation induced by a semiellipse is the same as flow over a gradually sloping surface for which the flow separation is caused by the interaction between the viscous force, the pressure force, and the turbulence level. For flow over bluff bodies, a downstream recirculation bubble is created which increases the aspect ratio and/or the turbulence level results in flow reattachment close behind the obstacle.

Shieh, C. F.↗

NASA NTRS1982

The far-infrared disk of M51

Far-infrared maps and multifrequency photometry are presented for M51 and its companion galaxy NGC 5195. Dust reradiates about half the starlight of the M51 + NGC 5195 system to produce the observed far-infrared (80-200 microns) luminosity of 3 x 10 to the 10th solar luminosities. Observed with 49-arcsec resolution and covering 37 arcmin-squared, the maps show that roughly 70% of this luminosity is produced by the 5 arcmin (approximately 15 kpc) wide far-infrared disk of M51. Comparable luminosities emitted from the central regions (diameters = 49 arcsec or 2.3 kpc) of M51 and NGC 5195 contribute the remaining 30% (approximately 1 x 10 to the 10th solar luminosities). The photometry reveals a difference in energetics at the galactic scale; dust producing the central luminosity of NGC 5195 classified as Ip-Ep, Irr II or SBa(r) is much less abundant and considerably warmer than the approximately 20 K dust producing the central luminosity of M51 (Sc I). Far-infrared properties are given for several galactic scale complexes of star formation in M51. Relationships are discussed for selected maps of optical starlight and emissions from these components of M51's interstellar medium: dust grains, CO molecules, hydrogen atoms, electrons, and H II regions.

Smith, J.↗

NASA NTRS1983

Axial-compressor flow distortion with water ingestion

The objective of the investigation is as follows: to establish relations between the steady state mean flow distortion generated during water ingestion into an axial-flow compressor and (a) characteristic length and time scales pertaining to (1) the centrifugal action and (2) the heat and mass transfer processes and (b) aerodynamic parameters based on blade geometry, aspect ratio and blade loading. Analytical and experimental results are presented for a small compressor to illustrate the extent of the distortion introduced as a function of (1) the operating speed and (2) the mass-based water content in the ingested mixture. Methods of scaling the effects in compressors of different sizes are discussed.

Tsuchiya, T.↗

NASA NTRS1984

LANDSAT 4 investigations of Thematic Mapper and multispectral scanner applications

The optimum index factor package was used to choose TM band for color compositing. Processing techniques were also used on TM data over several sites to: (1) reduce the amount of data that needs to be processed and analyzed by using statistical methods or by combining full-resolution products with spatially compressed products; (2) digitally process small subareas to improve the visual appearance of large-scale products or to merge different-resolution image data; and (3) evaluate and compare the information content of the different three-band combinations that can be made using the TM data. Results indicate that for some applications the added spectral information over MSS is even more important than the TM's increased spatial resolution.

Lauer, D. T.↗

NASA NTRS1984

Compression failure mechanisms in unidirectional composites

Compression failure mechanisms in unidirectional composites were examined. Possible failure modes of constituent materials are summarized and analytical models for fiber microbuckling are reviewed from a unified viewpoint. Due to deficiencies in available models, a failure model based on nonlinear properties and initial fiber curvature is proposed. The effect of constituent properties on composite compression behavior was experimentally investigated using two different graphite fibers and four different epoxy resins. The predominant microscopic scale failure mode was found to be shear crippling. In a soft resin, shear crippling was in the form of buckling of fibers on a microscopic scale. However, stiff resins failure was characterized by the formation of a kink band. For unidirectional laminates, compressive strength, and compressive modulus to a less extent, were found to increase with increasing magnitude of resin modulus. The change in compressive strength with resin modulus was predicted using the proposed nonlinear model.

Hahn, H. T.↗

NASA NTRS1984

The vertical structure and stability of alpha model accretion disks

In order to understand the physical processes that determine the time-dependent characteristics of accretion disks, a parameter investigation is conducted of the vertically explicit structure corresponding to steady state, alpha-model thin disk accretion for accreting objects of 1 solar mass. Attention is given to the role of convection in the vertical structure and the location of critical points representing the onset of thermal instability, as well as optically thin conditions. It is shown that the temperature in quiescence is likely to be low for most of the matter, and scaling laws are presented for the fundamental properties of the vertically explicit models from which the time scales for various idealized phenomena are derived. The ordering of three disk time scales obtained should allow discrimination among different models.

Cannizzo, J. K.↗

NASA NTRS1985

Planetary wave-mean flow interaction in the stratosphere: A comparison between the Northern and Southern Hemispheres

Based on satellite-derived data supplied by the National Meteorological Center (NMC), the dynamical interaction between planetary waves and mean zonal winds in the stratosphere is investigated. Special attention is paid to the differences between the Northern Hemisphere (NH) and the Southern Hemisphere (SH). An analysis is made using Eliassen-Palm (E-P) flux diagnostics for the period from June 1981 to May 1982. In a climatological sense, different seasonal evolutions of large-scale motions between the NH and the SH in the stratosphere are demonstrated. Vertical cross-section analysis is presented to show the day-to-day variation in the mean zonal wind and wave activity, in particular, the following phenomena: (1) the poleward shifting of the westerly jet, and (2) episodes after the shifting of the westerly jet.

Shiotani, M.↗

NASA NTRS1986

Compression failure mechanisms in unidirectional composites

Hahn, H. T.↗

NASA NTRS1987

Application of a sensitivity analysis technique to high-order digital flight control systems

A sensitivity analysis technique for multiloop flight control systems is studied. This technique uses the scaled singular values of the return difference matrix as a measure of the relative stability of a control system. It then uses the gradients of these singular values with respect to system and controller parameters to judge sensitivity. The sensitivity analysis technique is first reviewed; then it is extended to include digital systems, through the derivation of singular-value gradient equations. Gradients with respect to parameters which do not appear explicitly as control-system matrix elements are also derived, so that high-order systems can be studied. A complete review of the integrated technique is given by way of a simple example: the inverted pendulum problem. The technique is then demonstrated on the X-29 control laws. Results show linear models of real systems can be analyzed by this sensitivity technique, if it is applied with care. A computer program called SVA was written to accomplish the singular-value sensitivity analysis techniques. Thus computational methods and considerations form an integral part of many of the discussions. A user's guide to the program is included. The SVA is a fully public domain program, running on the NASA/Dryden Elxsi computer.

Paduano, James D.↗

NASA NTRS1987

Structural tailoring of advanced turboprops

A computer program has been developed for the performance of numerical optimizations of highly swept propfan blades by minimizing an objective function that is defined either as direct operating cost or the aeroelastic difference between a blade and its scaled model. Three component analysis categories are employed: an optimization algorithm, approximate analysis procedures for objective function and constraint evaluation, and refined analysis procedures for optimum design validation. The analyses conducted by the program encompass aerodynamic efficiency evaluation, finite element stress and vibration analysis, acoustics, flutter, and forced response life prediction.

Brown, K. W.↗