Measurements of the pressure distribution on swept back wings with trailing edge split flaps: summary of wind tunnel work at the College of Aeronautics 1948

Babister, A. W.2012-06-142012-06-141951-03http://dspace.lib.cranfield.ac.uk/handle/1826/7227This is an interim report giving measurement s that have so far been made of pressure distribution on two untapered wings swept back 45◦, aspect ratio 2 and 4, fitted with both full span and part span trailing edge split flaps. The Reynolds number in these tests was about 0.5x106.enMeasurements of the pressure distribution on swept back wings with trailing edge split flaps: summary of wind tunnel work at the College of Aeronautics 1948 - 50Report