Pressure plotting tests in the Royal Aircraft Establishment high speed wind tunnel on a 21 per cent thick, low drag aerofoil (Brabazon 1 wing root section)

Abstract

Pressure plotting tests have been made on the 21 per cent thick wing root section for the Brabazon I aircraft as a two-dimensional aerofoil spanning the Royal Aircraft Establishment High Speed Tunnel The tests covered a Mach number range up to 0.7 at a Reynolds number of about 3 x 10power6 and low speed tests were extended up to R =9.45 x 10power6. It appears that there is adequate margin between the cruising and stalling conditions to provide manoeuvrability and safety in up-gusts. The results ... may be pessimistic because the tunnel tests had to be made by covering the speed range at a series of certain fixed incidences. Also the incidence range covered was not large enough.