LAMINAR HEAT TRANSFER TO A TWO-DIMENSIONAL BLUNT FLAT NOSED BODY IN TRANSONIC AND SUPERSONIC FLOW
Abstract
Heat transfer rates are measured on a two-dimensional, blunt, flat nose and in the separated and reattaching flow regions of the separation bubble behind the leading edge corners in the high enthalpy laminar transonic and supersonic flow in the shock tube. The measurements are carried out in a shock Mach number range from 2.5 to 10, and a corresponding flow Mach number from approximately 0.4 (the flow being choked) to 2.7. The Reynolds number, which is based on half of the nose height, varies from 800 to 33,000 and the local Reynolds number on the flat plate section, behind the leading edge corners, based on the distance from the stagnation point varies from 1000 to 150,000. The results are correlated as functions of Mach and Reynolds numbers and stagnation to wall enthalpy ratios. The variations of local maximum and average heat transfer rates on the nose section and in the separation bubble region behind the corner are presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0664574
Entities
People
- Arnan Seginer
- Josef Rom
Organizations
- Technion – Israel Institute of Technology