Use of the Boundary Layer of a Cone to Measure Supersonic Flow Inclination
Abstract
An instrument is suggested for the measurement of supersonic flow inclination, taking advantage of the effect of angle of attack on the meridional velocity profile of the laminar boundary layer on a cone. This effect of angle of attack may be measured by the difference of total pressure recorded by two probes pointing toward the apex and located in the plane of symmetry of the flow. The theoretical response to angle of attack is derived and found to depend essentially on the ratio of angle of attack to cone semivertex angle. Thus, the more slender the cone, the greater the sensitivity to angle of attack, subject to restrictions imposed by the displacement effect of the boundary layer. Results of a single test are presented and discussed. The results show that sensitivity is limited to angles of attack less than the cone semivertex angle. The effect of probe size is discussed. Equations are presented which permit the probes to be located in such a way that maximum sensitivity is obtained. A method is described whereby the instrument may be calibrated for zero flow inclination.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1952
- Accession Number
- ADA377175
Entities
People
- Franklin K. Moore
Organizations
- National Aeronautics and Space Administration