TY - GEN
T1 - Linear Stability Investigation of Cross-Flow Instability for a Supersonic Swept Wing with a Biconvex Airfoil
AU - Haas, Anthony P.
AU - Hader, Christoph
AU - Fasel, Hermann F.
N1 - Funding Information:
This work was supported by ARO Grant W911NF-20-S-0006, with Dr. Matthew Munson serving as the program manager. Computer time was provided by the US Army Engineering Research and Development Center (ERDC) under the Department of Defense (DOD) High Performance Computing Modernization Program (HPCMP). The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the Army Research Office or the U.S. Government.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - The linear disturbance development of cross-flow instability for compressible flows on infinite span swept wings with a biconvex airfoil is investigated using Linear Stability Theory (LST). The main goal of the investigations was to explore the effects of the wing sweep angle and the airfoil thickness to chord ratio, and to provide a general overview of the linear cross-flow instability for the infinite span swept wing with biconvex airfoil. The LST results obtained indicate the presence of a strong cross-flow instability for the airfoils and sweep angles considered. As expected, the cross-flow instability becomes stronger for an increasing sweep angle and larger thickness to chord ratios of the airfoil. For outboard travelling modes (positive spanwise wavenumbers), it was shown that unsteady cross-flow disturbances became unstable further upstream than steady disturbances. On the other hand, for inboard travelling modes (negative spanwise wavenumbers), steady cross-flow disturbances became unstable further upstream than unsteady disturbances. Overall, the unsteady cross-flowdisturbances with positive spanwise wavenumbers had the largest growth rates and N-factors.
AB - The linear disturbance development of cross-flow instability for compressible flows on infinite span swept wings with a biconvex airfoil is investigated using Linear Stability Theory (LST). The main goal of the investigations was to explore the effects of the wing sweep angle and the airfoil thickness to chord ratio, and to provide a general overview of the linear cross-flow instability for the infinite span swept wing with biconvex airfoil. The LST results obtained indicate the presence of a strong cross-flow instability for the airfoils and sweep angles considered. As expected, the cross-flow instability becomes stronger for an increasing sweep angle and larger thickness to chord ratios of the airfoil. For outboard travelling modes (positive spanwise wavenumbers), it was shown that unsteady cross-flow disturbances became unstable further upstream than steady disturbances. On the other hand, for inboard travelling modes (negative spanwise wavenumbers), steady cross-flow disturbances became unstable further upstream than unsteady disturbances. Overall, the unsteady cross-flowdisturbances with positive spanwise wavenumbers had the largest growth rates and N-factors.
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U2 - 10.2514/6.2021-2848
DO - 10.2514/6.2021-2848
M3 - Conference contribution
AN - SCOPUS:85123375156
SN - 9781624106101
T3 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
Y2 - 2 August 2021 through 6 August 2021
ER -