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The nonlinearity of lift increase exits at high angles of attack in hypersonic state for double swept waverider. Shock wave attachment degree influenced by the leading edge sweep angle is the main factor for the nonlinearity other than vortex effect. When the shock wave detaches, the increase of the lift is approximately linear.
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This page is a summary of: Nonlinearity Analysis of Increase in Lift of Double Swept Waverider, AIAA Journal, January 2020, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.j058405.
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