THE EFFECTS OF FLOW THROUGH AN AIRCRAFT PITOT-STATIC PROBE AT SUPERSONIC MACH NUMBERS
Abstract
Tests of a standard, aircraft-type, pitot-static probe were conducted in a 12-in. supersonic tunnel to evaluate the effects on the probe total and static pressures resulting from drawing flow from the tube or putting flow into the tube. The data were obtained with the probe at zero angle of attack in a supersonic stream at Mach numbers from 1.5 to 5, and the Reynolds number per inch ranged from 120,000 to 580,000. The results are presented in terms of the ratio of measured probe pressure to the pressure for no tube flow as a function of a nondimensional parameter representing the quantity of flow being passed through the tube.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1966
- Accession Number
- AD0477832
Entities
People
- A. L. Baer
Organizations
- Arnold Engineering Development Complex