Theory of Ice Nucleation in Sonic and Supersonic Nozzles.
Abstract
The flow of air at the throat of a nozzle will have a Mach number of 1.0, when the stagnation pressure upstream of the throat is 1.9 times environment pressure of the exhaust region. If the stagnation pressure is greater than this critical value, a properly designed nozzle will support supersonic velocities in a region downstream of the throat. This paper is a preliminary draft of an attempt to organize the theoretical considerations involved in the development of ice embryos within supersonic nozzles, so that it will be possible to engineer effective ice nucleating nozzles for clearing supercooled fog.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1967
- Accession Number
- AD0778614
Entities
People
- C. J. Todd
- E. E. Hindman Ii