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  • 1
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    On the extrapolation of measured near field pressure signatures of unconventional configurations (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Extrapolation of measured overpressure data for predicting sonic boom characteristics of different aerodynamic configurations
    Keywords: AIRCRAFT
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    An evaluation of the far field overpressure integral. (1965)
    In:  Other Sources
    Details
    Publication Date: 2011-08-10
    Description: Exact equation for cross-sectional area distribution of maximum sonic boom over pressure at zero lift for two configurations
    Keywords: FLUID MECHANICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic analysis of three advanced configurations using the TranAir full-potential code (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Computational results are presented for three advanced configurations: the F-16A with wing tip missiles and under wing fuel tanks, the Oblique Wing Research Aircraft, and an Advanced Turboprop research model. These results were generated by the latest version of the TranAir full potential code, which solves for transonic flow over complex configurations. TranAir embeds a surface paneled geometry definition in a uniform rectangular flow field grid, thus avoiding the use of surface conforming grids, and decoupling the grid generation process from the definition of the configuration. The new version of the code locally refines the uniform grid near the surface of the geometry, based on local panel size and/or user input. This method distributes the flow field grid points much more efficiently than the previous version of the code, which solved for a grid that was uniform everywhere in the flow field. TranAir results are presented for the three configurations and are compared with wind tunnel data.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 437-452
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Some effects of Mach number and geometry on sonic boom (1967)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Hypersonic Aircraft Technol.; p 171-180
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Adaptive-wall wind-tunnel research at Ames Research Center (1982)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Adaptive-wall wind-tunnel research is summarized. This research includes small-scale two- and three-dimensional wind-tunnel experiments and numerical experiments with a three-dimensional adaptive-wall simulator. Airflow through the test-section walls is controlled by adjusting the pressures in segmented plenums. Interference free conditions are successfully attained in subsonic and transonic flows. An adaptive wall test section is constructed for the transonic wind tunnel. Wall interference was reduced in the three dimensional experiment at several angles of attack at Mach 0.60. A wing on wall configuration was modeled in the numerical experiments. These flow simulations showed that free air conditions can be approximated by adjusting boundary conditions at only the floor and ceiling of the test section. No sidewall control was necessary.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD Wall Interference in Wind Tunnels; 13 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    A numerical simulation of three-dimensional flow in an adaptive wall wind tunnel (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerical simulations of three dimensional flows in a prototype adaptive wall wind tunnel are conducted at the Mach number of 0.6 to investigate: (1) wind tunnel wall interference, (2) active streamline control by varying air removal or injection along the walls, and (3) to develop a method for establishing wall boundary conditions for interference free flows. Wind tunnel wall interference could be controlled by using only the vertical velocity components. For the configuration tested, interference free flow with solid sidewalls can be approximated by using only floor and ceiling blowing/suction.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2351 , A-9622 , NAS 1.60:2351
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Sonic boom pressure signatures for the space shuttle launch vehicle (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sonic boom pressure signatures were measured in supersonic and hypersonic wind tunnels for models of the space shuttle launch vehicle at 0 deg angle of attack with and without solid body simulations of the exhaust plumes. Data were measured at 30 deg increments in roll angle from 90 deg to 180 deg at Mach numbers from 3.02 to 5.56.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62441 , A-6092
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A Wind Tunnel Flight Correlation of Apollo 15 Sonic Boom (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A correlation of sonic boom pressure signatures recorded during reentry of the Apollo 15 command module with wind-tunnel signatures extrapolated to flight distances has been made for Mach numbers of 1.16 and 4.57. The flight pressure signatures were recorded by pressure sensors located onboard ships positioned near the ground track while the wind-tunnel signatures were measured during tests of a 0.016-scale model of the command module. The agreement between estimates based on wind-tunnel data and flight measurements was better at Mach 4.57 than at Mach 1.16.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62111
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Oblique-wing sonic boom (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to determine the magnitude of the groundtrack overpressure generated by an oblique-wing transport cruising at Mach 1.4 at 45,000 ft. A conventional swept-wing configuration was included in the study to provide a basis of comparison for the oblique-wing configuration. The results of the investigation have shown that the oblique-wing configuration produces less sonic boom overpressure at cruise lift coefficient than the swept-wing vehicle.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62247
    Format: application/pdf
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  • 10
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    A wind tunnel flight correlation of Apollo 16 sonic boom (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A correlation of sonic boom pressure signatures recorded during reentry of the Apollo 16 command module with wind-tunnel signatures extrapolated to flight distances was made for Mach numbers of 1.83 and 9.71. The flight pressure signatures were recorded by microphones located onboard ships positioned near the ground track, whereas the wind tunnel signatures were measured during a test of a 0.016-scale model of the command module. The agreement between estimates based on wind tunnel data and flight measurements was good at the tested Mach numbers.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62073
    Format: application/pdf
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