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  • Acoustics  (1)
  • Aircraft Design, Testing and Performance  (1)
  • 1
    facet.materialart.
    Unknown
    Effect of Reduced Frequency on Super Maneuver Delta Wing (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The unsteady, three-dimensional, Reynolds averaged Navier Stokes equations (NS) are used to simulate and study the flow response around a delta wing undergoing a pitch-up motion up to 90 degrees amplitude. The governing equations are solved time-accurately using the upwind. Roe flux-difference splitting, finite volume scheme. The primary model under consideration consists of a 76 degree swept, sharp-edged delta wing of zero thickness. The Reynolds number and Mach number are 0.45 X 10(exp 6) and .03 respectively. The wing is forced to pitch-up through a ramp function, using a wide range of reduced frequency to provide a good understanding of reduced frequency effect on high amplitude pitch maneuvers. Three reduced frequency values of .0834, 0.134 and 0.04, are used in this study. The computed results are compared with each other as well as the existing experimental data.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 98-0415 , Aerospace Sciences; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Focused and Steady-State Characteristics of Shaped Sonic Boom Signatures: Prediction and Analysis (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The objective of this study is to examine the effect of flight, at off-design conditions, on the propagated sonic boom pressure signatures of a small "low-boom" supersonic aircraft. The amplification, or focusing, of the low magnitude "shaped" signatures produced by maneuvers such as the accelerations from transonic to supersonic speeds, climbs, turns, pull-up and pushovers is the concern. To analyze these effects, new and/or improved theoretical tools have been developed, in addition to the use of existing methodology. Several shaped signatures are considered in the application of these tools to the study of selected maneuvers and off-design conditions. The results of these applications are reported in this paper as well as the details of the new analytical tools. Finally, the magnitude of the focused boom problem for "low boom" supersonic aircraft designs has been more accurately quantified and potential "mitigations" suggested. In general, "shaped boom" signatures, designed for cruise flight, such as asymmetric and symmetric flat-top and initial-shock ramp waveforms retain their basic shape during transition flight. Complex and asymmetric and symmetric initial shock ramp waveforms provide lower magnitude focus boom levels than N-waves or asymmetric and symmetric flat-top signatures.
    Keywords: Acoustics
    Type: NASA/CR-2011-217156 , NF1676L-12482
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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