1. 1Buchmann, O. “Thermal-Structural Design Study of an Airframe-Integrated Scramjet,” Tech. Rep. 3141, NASA,1979. Variable Name Value Units State Variable & Physics ρ Density - kg=m3ρu Mass Flow - kg=m2s E Energy Density - J=m3P Pressure - Pascalsγ Ratio of Specific Heats 1.4 Geometry A0 Minimum Cross Sectional Area of Engine 0.008 m2LI Inlet Length 0.5 m LC Combustor Length 0.1 m LE Expansion Region Length 0.1 m θI Angle of Inlet 0.0 Degrees θC Angle of Combustor 7.5 Degrees θE Angle of Expansion Region 15.0 Degrees Fueling φ Mixing Ratio variable fstoch Stochiometirc Fuel/Air Ratio 0.029 Hprop Fuel Heating Value 1:2×108J=Kg ρ0 Free Stream Density - Taken as Inflow Density 0.159 kg=m3u0 Free Stream Velocity - Take as Inflow Velocity 1300.0 m=s P0 Free Stream Pressure - Take as Inflow Pressure 47842.0 Pascals T Fuel Cycle Length variable s b Fuel Burst Length variable s Numerics Nxs Number of Grid Points 200 βCFL CFL Number 0.8 Order Order of ENO-Method 1 t0 Burn-In Time 0.5 ms
2. Number of Fuel Cycles to Predict Ahead with Slope 6 δT Increase / Decrease Factor for Fuel Cycle 0.1 δb;dec Decrease Factor for Fuel Burst Length 0.5 δb;inc Increase Factor for Fuel Burst Length 0.1 αmax Maximum Allowed Slope of Shock-Front xmin Left Boundary to Contain Shock-Front -0.35 m xmax Right Boundary to Contain Shock-Front -0.1 m Stochastic Parameterizations `t Correlation Length of Fueling Noise in Time 0.0001 s `x Correlation Length of Fueling Noise in Space 0.01666 m `i Correlation Time of Inflow Noise in Time 2 ms σf Percent Noise Added to Fueling Field 0.1 σin Percent Noise Added to Inflow Mach Number 0.1
3. Study on steady and unsteady unstart phenomena due to compound choking and/or fluctuations in combustor of scramjet engines
4. Control theory based airfoil design using the Euler equations
5. Volume 1;Shapiro A. H.,1953