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 ...
CONTENTS. Repeated Loading and Fatigue Tests on a D.H.104 (Dove) Wing and Fin. Shock-wave and Boundaiy-layer Phenomena near a Flat Surface. Jet Flow and its Effects on Aircraft. A Shielded Hot-wire Anemometer for Low Speeds. ...
Note: All papers discussed by the Aeronautical Research Council and recommended by them for external publication after 1st April, 1932, have been published in abstract only in the Reports and Memoranda Series.
CONTENTS: Spring Tabs on Frise Ailerons. Why Shear Webs? A Boundary Value Problem for a Hyperbolic Differential Equation Arising in the Theory of the Non-uniform Supersonic Motion of an Aerofoil. A Study by a Double-refraction ...
Note.--All papers discussed by the Aeronautical Research Council and recommended by them for external publication after 1st April, 1932, have been published in abstract only in the Reports and Memoranda Series. CONTENTS. ...
An experimental study has been made of two-dimensional turbulent boundary-layer flow with zero pressure gradient. The investigation was made to determine the accuracy of a method proposed by Preston for measuring the local ...
An accurate method of solution is developed for steady incompressible laminar boundary layers whose main-stream velocity U(x) is expressible as an odd polynomial in distance x measured along the wall. The velocity distribution ...
Supersonic wind tunnel tests were made over an incidence range from -4 to +30 degrees for a range of roll angles on a scrims of conical slender delta wing and body combinations with a short afterbody on which a rectangular ...