NEAR WAKE OF A SLENDER CONE AT LARGE ANGLE OF ATTACK
Abstract
The near wake of a sharp, slender cone at an angle of attack equal to the half-cone angle (10 deg) is studied experimentally. Tests were run at two different Reynolds numbers; these correspond to (1) completely laminar flow on the surface (Re = 150,000) and, (2) laminar flow on the windward and turbulent on the leeward surface (Re = 550,000). The nature of the surface boundary layer was determined by measuring the surface heat transfer over a wide range of test Reynolds numbers (60,000 < or = Re < or = 1,200,000) and comparing the data with theoretical analyses. Wake data obtained correspond to radial profiles taken in the plane of symmetry; total temperature, pitot, and static pressures are measured from the rear stagnation point to approximately seven diameters downstream of the base. Centerline distributions of Mach number, stagnation pressure, and static temperature are computed and compared to the corresponding results at zero angle of attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1968
- Accession Number
- AD0673953
Entities
People
- E. M. Schmidt
- Robert J. Cresci
Organizations
- New York University Tandon School of Engineering