Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing PDF Download

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Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing

Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing PDF Author:
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Languages : en
Pages : 25

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Book Description
Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.