THRUST VECTORING. SHOCK-WAVE AND PRESSURE EFFECTS OF COLD-AIR INJECTION INTO A TWO-DIMENSIONAL NOZZLE
Abstract
Experiments were done in which a small stre of cold air was injected into the Mach 1.86 section of a two-dimensional, glass-walled nozzle having a 1.0- by 0. -inch rectangular throat. Shadowgraphs of resultant shocks were taken and wall pressures in the nozzle measured. Mainstream stagnation pressure was fixed at 500 psig; injectant stagn tion pressure was varied from 125 to 1,000 psig. Shock-wave angle increased with incr asi g injecta pressure. Theoretical calculations of change of transverse momentum flux across an oblique circularcylindrical shock and across an oblique pl ne shock were completed, and results presented include formulas and graphs. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1961
- Accession Number
- AD0267465
Entities
People
- G.g. Barnes
- L.t. Bankston
Organizations
- Naval Air Weapons Station China Lake