Experiments with static tubes in a supersonic airstream -- parts 1 and 2

Abstract

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 of the tube to the flow. Pressure measurements have also been made in the vicinity of a shock wave and close to a wall. PART II. A family of flat-nosed pitot-tubes has been tested at Mach numbers of 1.6 and 1.8. At both Mach numbers it was found that no change of reading could be detected when the ratio of the external diameter to the bore was varied from 2 to 16. The Mach number calculated from the pitot pressure on the assumption that the bow wave ahead of the pressure hole was normal to the stream is, to within about ±½ per cent, equal to that calculated from the reading of a static tube.