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  • 1
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    One application of mega-geomorphology in education (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: One advantage of a synoptic view displaying landform assemblages provided by imagery is that one can often identify geomorphic processes which have shaped the region and which may affect the habitability of the area over a human life time. Considering the continued growth of the world population and the resultant pressure and the exploitation of land, usually without any consideration given to geologic processes, it is imperative that we attempt to educate as large a segment of the population as we can about geologic processes and how they influence land use. Space platform imagery which exhibits regional landscapes can be used: (1) to show students the impact of geologic processes over relatively short periods of time (e.g., the Mount St. Helens lateral blast); (2) to display the effects of poor planning because of a lack of knowledge of the local geologic processes (e.g., the 1973 image of the Mississippi River flood around St. Louis, MO); and (3) to show the association of certain types of landforms with building materials and other resources (e.g., drumlins and gravel deposits).
    Keywords: GEOPHYSICS
    Type: NASA. Goddard Space Flight Center Global Mega-Geomorphology; p 56-58
    Format: application/pdf
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  • 2
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    Measurement of airfoil heat transfer coefficients on a turbine stage (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The primary basis for heat transfer analysis of turbine airfoils is experimental data obtained in linear cascades. A detailed set of heat transfer coefficients was obtained along the midspan of a stator and a rotor in a rotating turbine stage. The data are to be compared to standard analyses of blade boundary layer heat transfer. A detailed set of heat transfer coefficients was obtained along the midspan of a stator located in the wake of a full upstream turbine stage. Two levels of inlet turbulence (1 and 10 percent) were used. The analytical capability will be examined to improve prediction of the experimental data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984; 8 p
    Format: application/pdf
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  • 3
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    Laser altimetry simulator. Version 3.0: User's guide (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A numerical simulator of a pulsed, direct detection laser altimeter has been developed to investigate the performance of space-based laser altimeters operating over surfaces with various height profiles. The simulator calculates the laser's optical intensity waveform as it propagates to and is reflected from the terrain surface and is collected by the receiver telescope. It also calculates the signal and noise waveforms output from the receiver's optical detector and waveform digitizer. Both avalanche photodiode and photomultiplier detectors may be selected. Parameters of the detected signal, including energy, the 50 percent rise-time point, the mean timing point, and the centroid, can be collected into histograms and statistics calculated after a number of laser firings. The laser altimeter can be selected to be fixed over the terrain at any altitude. Alternatively, it can move between laser shots to simulate the terrain profile measured with the laser altimeter.
    Keywords: GEOPHYSICS
    Type: NASA-TM-104588 , NAS 1.15:104588 , REPT-94B00039
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  • 4
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    The effects of Reynolds number, rotor incidence angle and surface roughness on the heat transfer distribution in a large-scale turbine rotor passage (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A combined experimental and computational program was conducted to examine the heat transfer distribution in a turbine rotor passage geometrically similar to the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP). Heat transfer was measured and computed for both the full span suction and pressure surfaces of the rotor airfoil as well as for the hub endwall surface. The objective of the program was to provide a benchmark-quality database for the assessment of rotor heat transfer computational techniques. The experimental portion of the study was conducted in a large scale, ambient temperature, rotating turbine model. The computational portion consisted of the application of a well-posed parabolized Navier-Stokes analysis of the calculation of the three-dimensional viscous flow through ducts simulating a gas turbine package. The results of this assessment indicate that the procedure has the potential to predict the aerodynamics and the heat transfer in a gas turbine passage and can be used to develop detailed three dimensional turbulence models for the prediction of skin friction and heat transfer in complex three dimensional flow passages.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-184260 , NAS 1.26:184260 , UTRC/R91-970057-3
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  • 5
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    The effects of inlet turbulence and rotor/stator interactions on the aerodynamics and heat transfer of a large-scale rotating turbine model, volume 1 (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A combined experimental and analytical program was conducted to examine the effects of inlet turbulence on airfoil heat transfer. Heat transfer measurements were obtained using low conductivity airfoils with miniature thermocouples welded to a thin, electrically heated surface skin. Heat transfer data were acquired for various combinations of low or high inlet turbulence intensity, flow coefficient (incidence), first-stator/rotor axial spacing, Reynolds number, and relative circumferential position of the first and second stators. Aerodynamic measurements include distributions of the mean and fluctuating velocities at the turbine inlet and, for each airfoil row, midspan airfoil surface pressures and circumferential distributions of the downstream steady state pressures and fluctuating velocities. Analytical results include airfoil heat transfer predictions and a examination of solutions of the unstead boundary layer equipment.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-4079 , E-3536 , NAS 1.26:4079 , UTRC-R86-956480-VOL-1
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  • 6
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    Measurement of airfoil heat transfer coefficients on a turbine stage (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A combined experimental and analytical program was conducted to examine the impact of a number of variables on the midspan heat transfer coefficients of the three airfoil rows in a one and one-half stage large scale turbine model. Variables included stator/rotor axial spacing, Reynolds number, turbine inlet turbulence, flow coefficient, relevant stator 1/stator 2 circumferential position, and rotation. Heat transfer data were acquired on the suction and pressure surfaces of the three airfoils. High density data were also acquired in the leading edge stagnation regions. Extensive documentation of the steady and unsteady aerodynamics was acquired. Finally, heat transfer data were compared with both a steady and an unsteady boundary layer analysis.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA, Lewis Research Center, Turbine Engine Hot Section Technology, 1987; p 169-179
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  • 7
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    The effects of turbulence and stator/rotor interactions on turbine heat transfer. II - Effects of Reynolds number and incidence (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Part I of this paper presents airfoil heat transfer data obtained in a rotating turbine model at its design rotor incidence. This portion of the paper presents heat transfer data obtained in the same model for various combinations of Reynolds number and inlet turbulence and for a very wide range of rotor incidence. On the suction surfaces of the first stage airfoils the locations and lengths of transition were influenced by both the inlet turbulence level and the Reynolds number. In addition it was demonstrated that on the first stage pressure surfaces combinations of high Reynolds number and high turbulence can produce heat transfer rates well in excess of two-dimensional turbulent flow. Rotor heat transfer distributions indicate that for relatively small deviations from the design incidence, local changes to the heat transfer distributions were produced on both pressure and suction sides near the stagnation region. For extremely large negative incidence the flow was completely separated from the rotor pressure surface producing very high local heat transfer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME PAPER 88-GT-5
    Format: text
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  • 8
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    The effects of inlet turbulence and rotor/stator interactions on the aerodynamics and heat transfer of a large-scale rotating turbine model. Part 4: Aerodynamic data tabulation (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A combined experimental and analytical program was conducted to examine the effects of inlet turbulence and airfoil heat transfer. The experimental portion of the study was conducted in a large-scale (approx. 5X engine), ambient temperature, rotating turbine model configured in both single-stage and stage-and-a-half arrangements. Heat transfer measurements were obtained using low-conductivity airfoils with miniature thermocouples welded to a thin, electrically heated surface skin. Heat transfer data were acquired for various combinations of low or high inlet turbulence intensity, flow coefficient, first stator-rotor axial spacing, Reynolds number and relative circumferential position of the first and second stators. Aerodynamic measurements obtained include distributions of the mean and fluctuating velocities at the turbine inlet and, for each airfoil row, midspan airfoil surface pressures and circumferential distributions of the downstream steady state pressures and fluctuating velocities. Results include airfoil heat transfer predictions produced using existing 2-D boundary layer computation schemes and an examination of solutions of the unsteady boundary layer equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-179469 , NAS 1.26:179469 , UTRC/R86-956480-4
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  • 9
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    The effects of turbulence and stator/rotor interactions on turbine heat transfer. I - Design operating conditions (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A combined experimental and analytical program was conducted to examine the effects of inlet turbulence, stator-rotor axial spacing, and relative circumferential spacing of first and second stators on turbine airfoil heat transfer. The experimental portion of the study was conducted in a large-scale (approximately 5X engine), ambient temperature, stage-and-a-half rotating turbine model. The data indicate that while turbine inlet turbulence can have a very strong impact on the first stator heat transfer, its impact in downstream rows is minimal. The effects on heat transfer produced by relatively large changes in stator/rotor spacing or by changing the relative row-to-row circumferential positions of stators were very small. Analytical results consist of airfoil heat transfer distributions computed with a finite-difference boundary layer code.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME PAPER 88-GT-125
    Format: text
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  • 10
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    Preliminary In-Flight Boundary Layer Transition Measurements on a 45 Deg Swept Wing at Mach Numbers Between 0.9 and 1.8 (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A preliminary flight experiment was flown to generate a full-scale supersonic data base to aid the assessment of computational codes, to improve instrumentation for measuring boundary layer transition at supersonic speeds, and to provide preliminary information for the definition of follow-on programs. The experiment was conducted using an F-15 aircraft modified with a small cleanup test section on the right wing. Results are presented for Mach (M) numbers from 0.9 to 1.8 at altitudes from 25,000 to 55,000 ft. At M greater than or = 1.2, transition occurred near or at the leading edge for the clean configuration. The furthest aft that transition was measured was 20 percent chord at M = 0.9 and M = 0.97. No change in transition location was observed after the addition of a notch-bump on the leading edge of the inboard side of the test section which was intended to minimize attachment line transition problems. Some flow visualization was attempted during the flight experiment with both subliming chemicals and liquid crystals. However, difficulties arose from the limited time the test aircraft was able to hold test conditions and the difficulty of positioning the photo chase aircraft during supersonic test points. Therefore, no supersonic transition results were obtained.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-100412 , H-1436 , NAS 1.15:100412
    Format: application/pdf
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