Air Condensation in Hypersonic Flow
- 1 August 1951
- journal article
- research article
- Published by AIP Publishing in Journal of Applied Physics
- Vol. 22 (8) , 1077-1083
- https://doi.org/10.1063/1.1700104
Abstract
The NOL 12×12‐cm hyperballistics wind tunnel No. 4, which operates in a Mach number range up to eleven, is briefly described. Experiments performed in this tunnel indicate that a fraction of the air condenses at or shortly after reaching the dew line for air condensation unless the supply air is preheated. The measured effects of air condensation on the flow at high Mach numbers for a variety of supply temperatures and pressures are given. It is found that of the flow parameters commonly measured in supersonic wind tunnels, only static‐pressure and shock‐angle measurements are sensitive to liquefaction effects. A simple thermodynamic analysis assuming a reversible condensation process allows interpretation of some of the observations.This publication has 4 references indexed in Scilit:
- Sixth Meeting of the Division of Fluid Dynamics at Urbana, Illinois, May 12, 13, 1950Physical Review B, 1950
- Results of Recent Hypersonic and Unsteady Flow Research at the Langley Aeronautical LaboratoryJournal of Applied Physics, 1950
- Sublimation in a Wilson chamberProceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences, 1947
- AN INVESTIGATION OF THE COEXISTING LIQUID AND VAPOR PHASES OF SOLUTIONS OF OXYGEN AND NITROGEN1Journal of the American Chemical Society, 1927