Computational Design Methodology of Adaptive Outer Mold Line for Robust Low En-Route Noise of a Supersonic Aircraft-Reference-Cited by-同舟云学术

Computational Design Methodology of Adaptive Outer Mold Line for Robust Low En-Route Noise of a Supersonic Aircraft

Published:2021-01-04 Issue: Volume: Page:
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Container-title:AIAA Scitech 2021 Forum
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Author:

Weaver-Rosen Jonathan M.¹,Carpenter Forrest L.¹,Cizmas Paul G.¹,Malak Richard J.¹,Abraham Troy A.²,Hunsaker Douglas F.²,Lazzara David S.³

Affiliation:

1. Texas A&M University

2. Utah State University

3. The Boeing Company

Publisher

American Institute of Aeronautics and Astronautics

Reference41 articles.

1. Magee, T. E., Wilcox, P. A., Fugal, S. R., Acheson, K. E., Adamson, E. E., Bidwell, A. L., and Shaw, S. G. “System-Level Experimental Validations for Supersonic Commercial Transport Aircraft Entering Service in the 2018-2020 Time Period: Phase I Final Report,” Technical Report NASA/CR-2013-217797, NASA Langley Research Center, 2013.

2. Magee, T. E., Fugal, S. R., Fink, L. E., Adamson, E. E., and Shaw, S. G. “System-Level Experimental Validations for Supersonic Commercial Transport Aircraft Entering Service in the 2018-2020 Time Period: Phase II Final Report,” Technical Report NASA/CR-2015-218983, NASA Langley Research Center, 2015.

3. Boeing N+2 Supersonic Experimental Validation Phase II Program

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