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FOUR SHILLINGS NETExperiments with Static Tubes

By Parts I, D. W. Holder, B. Sc, R. J. North and A. Chinneck

Abstract

Summary.--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 of the tube to the flow. Pressure measurements have also been made in the vicinity of a shock wave and close to a wall. 1. I~troduction.--Although they are in everyday use ill supersonic tunnels, few accounts of systematic experiments on the design of static tubes for measurements in supersonic flows seem to have been published. The present tests were not intended to be comprehensive, but to indicate at one Maeh number (1.6) and one Reynolds number (3 × l0 b based on the external diameter of the tube), the order of magnitude of the effects of some of the variables which are known to be important. It is hoped that the results, will be of value as a basis for the further experiments which may be required for the design of static tubes for use under conditions which differ widely from those of the present tests. 2. Apparatus and Technique.--The tests were made in the National Physical Laboratory 9 × 3 in. Induced-Flow Wind-Tunnel R. & M. 278P which for this purpose was fitted with a nozzle designed to give a Mach number of 1.6. It was decided to conduct the investigation at a Reynolds number similar to that of a tube which could be used during routine tests in

Year: 2012
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