Evaluation of screech suppression concepts in a 20,000-pound-thrust hydrogen--oxygen rocket
Technical Report
·
OSTI ID:5174817
None
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, Ohio (USA). Lewis Research Center
- OSTI ID:
- 5174817
- Report Number(s):
- N-67-34758; NASA-TM-X-1435
- Country of Publication:
- United States
- Language:
- English
Similar Records
Experimental investigation of acoustic liners to suppress screech in hydrogen-oxygen rockets
Effect of thrust per element on combustion stability characteristics of hydrogen--oxygen rocket engines
Ignition of hydrogen-oxygen rocket combustor with chlorine trifluoride and triethylaluminum. [Ignition characteristics of 125-lb thrust cold gaseous hydrogen liquid oxygen rocket combustor]
Technical Report
·
Tue Jan 31 23:00:00 EST 1967
·
OSTI ID:5144491
Effect of thrust per element on combustion stability characteristics of hydrogen--oxygen rocket engines
Technical Report
·
Tue Oct 01 00:00:00 EDT 1968
·
OSTI ID:5174807
Ignition of hydrogen-oxygen rocket combustor with chlorine trifluoride and triethylaluminum. [Ignition characteristics of 125-lb thrust cold gaseous hydrogen liquid oxygen rocket combustor]
Technical Report
·
Fri Mar 31 23:00:00 EST 1961
·
OSTI ID:5167131