RECOMBINATION OF HYDROGEN-AIR COMBUSTION PRODUCTS IN AN EXHAUST NOZZLE
Abstract
Thrust losses due to the inability of dissociated combustion gases to recombine in exhaust nozzles are of primary interest for evaluating the performance of hypersonic ramjets. Some results for the expansion of H-air combustion products are described. Combustion air was preheated up to 3300 R to simulate high-Mach-number flight conditions. Static-temperature measurements using the line reversal method and wall static pressures were used to indicate the state of the gas during expansion. Results indicated substantial departure from the shifting equilibrium curve beginning slightly downstream of the nozzle throat at stagnation pressures of 1.7 and 3.6 atmospheres. The results are compared with an approximate method for determining a freezing point using an over-all rate equation for the oxidation of H. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1961
- Accession Number
- AD0262039
Entities
People
- Erwin A. Lezberg
- Richard B. Lancashire
Organizations
- National Aeronautics and Space Administration