Experimental and analytical comparison of flowfields in a 110 N (25 Lbf) H2/O2 rocketA gaseous hydrogen/gaseous oxygen 110 N (25 lbf) rocket has been examined through the RPLUS code using the full Navier-Stokes equations with finite-rate chemistry. Performance tests were conducted on the rocket in an altitude test facility. Preliminary parametric analyses have been performed for a range of mixture ratios and fuel film cooling percentages. It is shown that the computed values of specific impulse and characteristic exhaust velocity follow the trend of the experimental data. Specific impulse computed by the code is lower than the comparable test values by about two to three percent. The computed characteristic exhaust velocity values are lower than the comparable test values by three to four percent. Thrust coefficients computed by the code are found to be within two percent of the measured values. It is concluded that the discrepancy between computed and experimental performance values could not be attributed to experimental uncertainty.
Document ID
19910061179
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Reed, Brian D. (NASA Lewis Research Center Cleveland, OH, United States)
Penko, Paul F. (NASA Lewis Research Center Cleveland, OH, United States)
Schneider, Steven J. (NASA Lewis Research Center Cleveland, OH, United States)
Kim, Suk C. (NASA Lewis Research Center Cleveland; Sverdrup Technology, Inc., Brook Park, OH, United States)