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An experimental study is presented to document the effect of partial span flaps on a slender delta wing. The lift increment was dependent on the flap span ratio raised to the power 0.613
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This page is a summary of: Experimental Evaluation of Partial-Span Flaps on a Seventy-Degree Delta Wing, Journal of Aircraft, September 2020, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.c036019.
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