Numerical Simulation of a C-D Rocket Nozzle - Fluent

As we know the preliminary part of numerical modelling is to simplify the Domain and the domain has been simplified. Too many contact surfaces inside Saturn V nozzle is suppressed and the certain boundary conditions are applied and the Boundary conditions will not be closer to original conditions.

CFD methodology : SST k-w Turbulence model

Boundary conditions : C.Chamber pressure : 4 MPA , Temperature : 1300 K , Fluid : Liquid O2, Pressure outlet and approximate Prop Flow rate - 80 kg/s

XY plot for Velocity has been plotted with respect to the domain position. I couldn't add the Animated video directly from the Device and in future i'll try to upload the work in some platforms. In order to optimize the nozzle effectiveness the formulas can be used according to the results

Pressure at throat
Pt = Pc × [1 + (k - 1) / 2]-k/(k-1)

Temp at throat
Tt = Tc × [1 / (1 + (k - 1) / 2)]

throat area
 At = (q / Pt) × SQRT[ (R' × Tt) / (M × k) ] 

Mach No
Nm2 = (2 / (k - 1)) × [(Pc / Pa)(k-1)/k - 1]

Nozzle Exit Area
Ae = (At / Nm) × [(1 + (k - 1) / 2 × Nm2)/((k + 1) / 2)](k+1)/(2(k-1))

Finally Thrust
Ve = SQRT[ (2 × k / (k - 1)) × (R' × Tc / M) × (1 - (Pe / Pc)(k-1)/k) ]

As we know for maximum thrust when Pe/Pa =1

since to make it short ,I have attached only the temperature contour and if any results needed don't hesitate to message me either in LinkedIn or ResearchGate. i don't want make it a mess by sharing all the results. thanks for stopping by and have a great day ahead !!

Warm regards

Aravinth Kamaraj