Dataset:  nasa1.dat

Source: R.S. Jankovsky, T.D. Smith, A.J. Pavli (1999). "High-Area-Ratio Rocket
Nozzle at High Combustion Chamber Pressure-Experimental and Analytical
Validation", NASA/TP-1999-208522

Description: Experiments with nozzle experiment area ratio and propellant
mixture ratios in rockets

Variables/Columns
Nozzle Area Ratio  5-8
Propellant Mixture Ratio  (O/F)  13-16  /* Oxidizer flow / fuel flow  */
Vacuum Thrust Coefficient  20-24
Vacuum Thrust Efficiency (%)  29-32
Vacuum Specific Impulse    36-40
Specific Impulse Efficiency  (%)   45-48