A shape optimization methodology for reducing the sonic boom initial pressure rise

Charbel Farhat; Kurt Maute; Brian Argrow; Melike Nikbay

doi:10.2514/6.2002-145

A shape optimization methodology for reducing the sonic boom initial pressure rise

Charbel Farhat
, Kurt Maute
, Brian Argrow
, Melike Nikbay

University of Colorado at Boulder

Research output: Contribution to conference › Paper › peer-review

20 Citations (Scopus)

Abstract

We present a shape optimization methodology for reducing the initial shock pressure rise (ISPR) on the ground of a supersonic aircraft. This methodology combines elements from the linearized aerodynamic theory such as Whitham's F-function with elements from the nonlinear aerodynamic theory such as the prediction of lift distribution by an Euler or a Navier-Stokes flow solver. We report on the application of this shaping technology to a Point of Departure aircraft developed by Lockheed-Martin for DARPA's Quiet Supersonic Platform program. We demonstrate a ten-fold reduction of the ISPR on the ground, from 1.623 psf at M_∞ = 1.5 to 0.152 psf, while maintaining constant lift and wave drag.

Original language	English
DOIs	https://doi.org/10.2514/6.2002-145
Publication status	Published - 2002
Externally published	Yes
Event	40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 14 Jan 2002 → 17 Jan 2002

Conference

Conference	40th AIAA Aerospace Sciences Meeting and Exhibit 2002
Country/Territory	United States
City	Reno, NV
Period	14/01/02 → 17/01/02

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10.2514/6.2002-145

Cite this

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abstract = "We present a shape optimization methodology for reducing the initial shock pressure rise (ISPR) on the ground of a supersonic aircraft. This methodology combines elements from the linearized aerodynamic theory such as Whitham's F-function with elements from the nonlinear aerodynamic theory such as the prediction of lift distribution by an Euler or a Navier-Stokes flow solver. We report on the application of this shaping technology to a Point of Departure aircraft developed by Lockheed-Martin for DARPA's Quiet Supersonic Platform program. We demonstrate a ten-fold reduction of the ISPR on the ground, from 1.623 psf at M∞ = 1.5 to 0.152 psf, while maintaining constant lift and wave drag.",

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AU - Argrow, Brian

AU - Nikbay, Melike

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N2 - We present a shape optimization methodology for reducing the initial shock pressure rise (ISPR) on the ground of a supersonic aircraft. This methodology combines elements from the linearized aerodynamic theory such as Whitham's F-function with elements from the nonlinear aerodynamic theory such as the prediction of lift distribution by an Euler or a Navier-Stokes flow solver. We report on the application of this shaping technology to a Point of Departure aircraft developed by Lockheed-Martin for DARPA's Quiet Supersonic Platform program. We demonstrate a ten-fold reduction of the ISPR on the ground, from 1.623 psf at M∞ = 1.5 to 0.152 psf, while maintaining constant lift and wave drag.

AB - We present a shape optimization methodology for reducing the initial shock pressure rise (ISPR) on the ground of a supersonic aircraft. This methodology combines elements from the linearized aerodynamic theory such as Whitham's F-function with elements from the nonlinear aerodynamic theory such as the prediction of lift distribution by an Euler or a Navier-Stokes flow solver. We report on the application of this shaping technology to a Point of Departure aircraft developed by Lockheed-Martin for DARPA's Quiet Supersonic Platform program. We demonstrate a ten-fold reduction of the ISPR on the ground, from 1.623 psf at M∞ = 1.5 to 0.152 psf, while maintaining constant lift and wave drag.

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T2 - 40th AIAA Aerospace Sciences Meeting and Exhibit 2002

Y2 - 14 January 2002 through 17 January 2002

ER -

A shape optimization methodology for reducing the sonic boom initial pressure rise

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