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  • AERODYNAMICS  (91)
  • INSTRUMENTATION AND PHOTOGRAPHY  (51)
  • 1995-1999
  • 1980-1984  (142)
  • 1970-1974
  • 1982  (142)
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  • 1995-1999
  • 1980-1984  (142)
  • 1970-1974
Year
  • 1
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    Tunable diode-laser heterodyne spectrometer for remote observations near 8 microns (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A diode-laser-based, ultrahigh resolution IR heterodyne spectrometer for laboratory and field use has been developed for operation between 7.5 and 8.5 microns. The local oscillator is a PbSe tunable diode laser kept continuously at operating temperatures of 12-60 K using a closed-cycle cooler. The laser output frequency is controlled and stabilized using a high-precision diode current supply, constant temperature controller, and a shock isolator mounted between the refrigerator cold tip and the diode mount. The system largely employs reflecting optics to minimize losses from internal reflection and absorption and to eliminate chromatic effects. Spectral analysis of the diode-laser output between 0 and 1 GHz reveals excess noise at many diode current settings, which limits the IR spectral regions over which useful heterodyne operation can be achieved. Observations have been made of atmospheric N2O, O3, and CH4 between 1170 and 1200/cm, using both a single-frequency swept IF channel and a 64-channel RF spectral line receiver with a total IF coverage of 1600 MHz.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 21; Jan. 15
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Tunable diode laser heterodyne spectrometer for remote observations near 8 microns (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Infrared heterodyne spectroscopy is a passive technique employing coherent optical detection for the study of spectral features in remote sources. It employs optical components such as mirrors and lenses normally associated with incoherent optics, but because of it's coherent nature, it offers the advantages of ultrahigh spectral resolving power, high frequency precision, and diffraction limited field-of-view. Attention is given to the development of an ultrahigh resolution diode laser heterodyne spectrometer for observational and laboratory use. The instrument is designed for operation in the spectral range from 7.5 to 8.5 microns. A PbSe tuneable diode laser (TDL) is employed as local oscillator. A closed-cycle cooler is employed to keep the oscillator at operating temperatures in the range from 12 to 60 K. Attention is given to factors determining the TDL heterodyne sensitivity, the spectrometer design, and a survey of 8 micron observations, SiO could be detected in the sunspot spectrum.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Instrumentation in astronomy IV; Fourth Conference; Mar 08, 1982 - Mar 10, 1982; Tucson, AZ
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    NASA Langley laminar flow control airfoil experiment (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The design and construction of an advanced swept supercritical airfoil for commercial aircraft to be tested in a transonic wind tunnel is described. The swept LFC airfoil was designed for a given thickness ratio and lift coefficient, with emphasis placed on high critical Mach number with shock-free flow. It is compatible with satisfactory low speed and buffeting characteristics and minimizing the suction laminarization. Further emphasis was placed on achieving shock-free flow over a wide range of off-design conditions including trailing edge flap control. The requirements and design of the suction system and modifications to the Langley 8 foot transonic pressure tunnel is briefly described. Contouring of nonporous test section walls for free air simulation and flow quality improvements is included.
    Keywords: AERODYNAMICS
    Type: Laminar Flow Control; p 1-42
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A digital optical torquemeter for high rotational speed applications (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A digital optical torquemeter system designed for applications at high rotational speeds was fabricated and tested for zero stability at speeds up to 20,000 rpm. Data obtained in a spin rig and with simulated inputs demonstrate that the system is capable of measuring torque bar twist to within 0.03 degrees at speeds of 30,000 rpm. The optical system uses fiber optic bundles to transmit light to the torque bar and to silicon avalanche detectors. The system is microcomputer based and provides measurements of average torque and torque as a function of angular shaft position. The torquemeter requires no bearings or other contact between the rotating torque bar and the nonrotating optics, and tolerates movement of the torque bar as large as 1 mm relative to the optics.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-82914 , E-1189 , NAS 1.15:82914
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Instrument manual for the retarding ion mass spectrometer on Dynamics Explorer-1 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The retarding ion mass spectrometer (RIMS) for Dynamics Explorer-1 is an instrument designed to measure the details of the thermal plasma distribution. It combines the ion temperature determining capability of the retarding potential analyzer with the compositional capabilities of the mass spectrometer and adds multiple sensor heads to sample all directions relative to the spacecraft ram direction. This manual provides a functional description of the RIMS, the instrument calibration, and a description of the commands which can be stored in the instrument logic to control its operation.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-82484 , NAS 1.15:82484
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Influence of surface static-pressure orifices on boundary-layer transition (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the interaction of a laminar boundary layer and surface static-pressure orifices was conducted on a natural laminar flow airfoil. The effects of both favorable and adverse pressure gradients were studied at Reynolds numbers based on airfoil chord from approximately 500,000 to 6,000,000 with Mach number varying accordingly from about 0.03 to 0.42. The smaller the diameter of the orifice, the less likely it will cause premature transition. Locating the orifices in a chord-wise row aligned with the flow appears to have an additive, adverse effect on transition. Tube length-to-orifice diameter ration does not seem to have a consistent influence on transition.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84492 , L-15109 , NAS 1.15:84492
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Wind-Tunnel/Flight Correlation, 1981 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel/flight correlation activities are reviewed to assure maximum effectiveness of the early experimental programs of the National Transonic Facility (NTF). Topics included a status report of the NTF, the role of tunnel-to-tunnel correlation, a review of past flight correlation research and the resulting data base, the correlation potential of future flight vehicles, and an assessment of the role of computational fluid dynamics.
    Keywords: AERODYNAMICS
    Type: NASA-CP-2225 , L-15368 , NAS 1.55:2225
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Experimental study of delta wing leading-edge devices for drag reduction at high lift (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag reduction devices selected for evaluation were the fence, slot, pylon-type vortex generator, and sharp leading-edge extension. These devices were tested on a 60 degree flatplate delta (with blunt leading edges) in the Langley Research Center 7- by 10-foot high-speed tunnel at low speed and to angles of attack of 28 degrees. Balance and static pressure measurements were taken. The results indicate that all the devices had significant drag reduction capability and improved longitudinal stability while a slight loss of lift and increased cruise drag occurred.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165846
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Subsonic panel method for the efficient analysis of multiple geometry perturbations (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An accurate and efficient method was developed for the aerodynamic analysis of a series of arbitrary small geometry perturbations to a given baseline configuration. The method is appropriate for wing-fuselage configurations in incompressible potential flow. Mathematical formulations are presented for three computer programs that are employed. The first program is a conventional surface panel method for calculating the baseline singularity distribution. The second program calculates a partial derivative matrix. Each element of the matrix is the rate of change of singularity strength at one point with respect to a surface coordinate of a different point. For each baseline configuration, the calculated quantities from the first two programs establish an input file for the third. The third program calculates the surface pressure distribution and forces and moments for a series of geometry perturbations.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3528
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Inlet and airframe compatibility for a V/STOL fighter/attack aircraft with top-mounted inlets (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force and inlet pressure data are obtained for 9.5% force and pressure models of a V/STOL fighter/attack aircraft configuration with top mounted twin inlets. Data are presented from tests conducted in the Ames Unitary Wind Tunnels at Mach numbers of 0.6, 0.9, and 1.2 at angles of attack up to 27 deg. and angles of sideslip up to 12 deg. Trimmed aerodynamic characteristics and inlet performance are compared for three different leading edge extension (LEX) configurations. The effects of wing leading and trailing-edge flaps on the inlet are also determined. Maneuver perfromance is calculated form combined force and inlet pressure data. The largest of the three LEX sizes tested gives the best airplane maneuver performance. Wing flap deflections improved inlet recovery at all Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84252 , A-8948 , NAS 1.15:84252
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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