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NIA Seminar by Osama Kandil |
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Date: November 15, 2005
Time: 10:30am
Location: NIA, Rm 137
Sonic Boom Prediction, Focusing and Mitigation
Osama Kandil, Old Dominion University
The Seminar addresses the capabilities of the newly-developed full-potential equation computer code by our research team at Old Dominion University/ Aerospace Engineering Department for prediction of sonic boom ground signature. This is a far less costly route for investigating the prediction and mitigation of the ground sonic boom noise in comparison with the field measurements cost. After initial successful applications for predicting sonic-boom ground noise of simple supersonic wings, it was decided to apply it to a complex configuration of a real aircraft. Northrop-Grumman Company has been conducting field measurements in California on a modified F-5E aircraft. The sonic-boom ground signature of the modified F-5E aircraft used in the F-5E “Shaped Sonic Boom Experiment” (SSBE) Program by Northrop-Grumman Company was predicted successfully. The predicted computational results of our computer code were in excellent agreement with the field measured data. Animation Movie was developed to show the shock system interaction from an altitude of 32,700 ft all the way to the ground.
The next issue of this work is the simulation of the sonic-boom focusing (superboom). Superboom develops when the aircraft accelerates, turns or maneuvers. With superboom conditions, the ground noise of sonic boom is magnified up to 2-3 times the original sonic boom noise, which could severely harm human ears and structures as well on the ground. For modeling the superboom problem, the nonlinear Tricomi equation is computationally solved. We have developed four computational schemes and the associated computer codes to simulate this problem. The results of these computer codes have shown successful prediction, and the results of the different codes have been in good agreement with each other. Moreover, animation movies were produced for more understanding of the physics of the superboom development.
For sonic boom mitigation, a study has been conducted to investigate the effect of increasing the wing dihedral angle on the ground sonic-boom noise. Reductions of the sonic boom ground noise ranged from 12 to 14 percent. Additional geometrical adjustments and optimization of the aircraft configuration are being investigated.
Research and development work conducted by our team is continuing for future design analysis with minimum human interference. The codes would be highly accurate and efficient with the use of our computer clusters in the Engineering and Computational Science Building.
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