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  • Other Sources  (10)
  • NASA Technical Reports  (10)
  • AERODYNAMICS  (6)
  • ATOMIC AND MOLECULAR PHYSICS  (4)
  • 1
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    Atomic oxygen dosimetry measurements made on STS-46 by CONCAP 2 (1995)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: With increasing flight duration and the possibility of a permanent facility in space, long-term monitoring of material degradation due to atomic oxygen is increasing in importance. Reliance on models to determine the fluence of atomic oxygen is not only necessarily complex but also imprecise due to the strong dependence of oxygen concentration on day/night, latitude and solar activity. Mass-spectroscopy, the traditional method for determining the gas phase species densities at low pressure, is not only expensive but is limited in the area that it can monitor. Our group has developed a simple and inexpensive dosimeter to measure the atomic oxygen fluence via the change in resistance as the sensor element is gradually oxidized. The sensors consisted of thin-film circuit elements deposited on a suitable substrate. Four-point resistance measurements were used to monitor the change in resistance. Results obtained using silver and carbon dosimeters flown on STS-46 (CONCAP 2-01) will be discussed.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: NASA. Langley Research Center, LDEF: 69 Months in Space. Third Post-Retrieval Symposium, Part 3; p 957-970
    Format: application/pdf
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  • 2
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    Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg sweep case and also for small angles of attack at the 67.5 deg sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
    Keywords: AERODYNAMICS
    Type: AGARD Unsteady Aerodynamics-Fundamentals and Applications to Aircraft Dynamics; 15 p
    Format: text
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  • 3
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    Fluorescence branching ratios from the A2Sigma + (v-prime = 0) state of NO (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The emission spectrum of NO from several rotational levels in the first excited state has been recorded. Branching ratios have been measured and Franck-Condon Factors calculated from the experimental data. Lifetimes of the lines used have been measured and Einstein A-values calculated.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer (ISSN 0022-4073); 29; April 19
    Format: text
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  • 4
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    Vibronic effects in the predissociation of the C/1/Pi/u state of C2N2 (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The partitioning of excess photochemical energy as a function of the vibrational energy of the state of C2N2 has been measured. Surprisal theory has been used to analyze the data and it shows that complete randomization does not occur before dissociation. The results are also inconsistent with the predictions of the quasidiatomic theory for photodissociation.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: Journal of Chemical Physics; 71; Dec. 1
    Format: text
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  • 5
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    Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 deg. and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg. sweep case and also for small angles of attack at the 67.5 deg. sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86677 , A-85119 , NAS 1.15:86677
    Format: application/pdf
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  • 6
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    Fixed-base simulation study of decoupled controls during approach and landing of a STOL transport airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed-base visual simulation study has been conducted to evaluate the use of decoupled controls as a means for reducing pilot workload during approach and landing of an externally blown jet-flap short take-off and landing (STOL) transport. All six rigid-body degrees of freedom were employed with the aerodynamic characteristics based on wind-tunnel data. The primary piloting task was to use a flight director to capture and maintain a two-segment glide slope, with a closed-circuit television display of a STOL airport used during simulations of the flare and landing. The decoupled longitudinal controls used constant prefilter and feedback gains to provide steady-state decoupling of flight-path angle, pitch angle, and forward velocity. The pilots were enthusiastic about the decoupled longitudinal controls but believed the decoupled concept offered no significant advantage over conventional controls in the lateral mode.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7363 , L-8825
    Format: application/pdf
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  • 7
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    Model for the solution of supersonic viscous interaction effects on blunted cones (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Mar. 197
    Format: text
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  • 8
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    Static-pressure contours in the blade passage at the tip of several high Mach number rotors (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static pressure contours of turbine rotor blade tips at high Mach numbers
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2170 , E-5875
    Format: application/pdf
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  • 9
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    Comparative performance tests on the Mod-2, 2.5-mW wind turbine with and without vortex generators (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A test program was conducted on the third Mod-2 unit at Goldendale, Washington, to systematically study the effect of vortex generators (VG's) on power performance. The subject unit was first tested without VG's to obtain baseline data. Vortex generators were then installed on the mid-blade assemblies, and the resulting 70% VG configuration was tested. Finally, vortex generators were mounted on the tip assemblies, and data was recorded for the 100% VG configuration. This test program and its results are discussed in this paper. The development of vortex generators is also presented.
    Keywords: AERODYNAMICS
    Type: DOE/NASA Workshop on Horizontal Axis Wind Turbine Technology; May 08, 1984 - May 10, 1984; Cleveland, OH; United States|DASCON Engineering, Collected Papers on Wind Turbine Technology; p 67-77
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  • 10
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    Time-resolved laser-induced fluorescence of selected even-parity 7p states of Xe I (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Lifetimes and self-quenching rates have been measured for excited states of Xe I that were populated using simultaneous two-photon absorption. Lifetimes measured in this study are somewhat shorter than those measured using the broadband-excitation technique. Lifetimes reported here are all faster than 100 nsec. Deactivation rates are approximately 2 x 10 to the -10th cu cm/sec per mol.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: Optical Society of America, Journal, B: Optical Physics (ISSN 0740-3224); 2; 414-416
    Format: text
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