A 9 X 3 in. high-speed wind tunnel driven by a compressed-air injector has been built in the Aerodynamics Division of the National Physical Laboratory. The tunnel operates at roughly atmospheric stagnation pressure and has ...

The present investigation was designed primarily to check the validity of a simple method which had been suggested for designing an aerofoil section on which, for a limited range of incidence, turbulent boundary-layer ...

PART I. Systematic.tests have been made at a Mach number of 1.6 on a family of static tubes. The variables which have been investigated are the shape of the nose, the distance of the holes downstream, and the inclination ...

The performance of a shock tunnel operated by the reflected-shock technique is examined theoretically neglecting viscous effects and high-temperature real-gas effects. Particular attention is given to disturbances to the ...