def make_pratv2L(oxName, fuelName, MR):
C = CEA_Obj(oxName=oxName, fuelName=fuelName)
machL = [C.get_Chamber_MachNumber(Pc=Pc, MR=MR, fac_CR=cr) for cr in crL]
gamL = [C.get_Chamber_MolWt_gamma(Pc=Pc, MR=MR)[-1] for cr in crL]
pratL = [1 + gam * M**2 for (gam, M) in zip(gamL, machL)]
plot(crL,
pratL,
label=r'%s/%s (1+$\gamma*M^2$)' % (oxName, fuelName),
linewidth=2)
from rocketcea.cea_obj import CEA_Obj # Calculate Reynolds number in Chamber and at Throat. ispObj = CEA_Obj( oxName='LOX', fuelName='MMH') Pc = 100 MR = 1.0 eps= 40 Rt = 1.0 # inches fac_CR = 2.5 frozen = 0 sonicL = ispObj.get_SonicVelocities( Pc=Pc, MR=MR, eps=eps, frozen=frozen) Mchm = ispObj.get_Chamber_MachNumber( Pc=Pc, MR=MR, fac_CR=fac_CR ) velChm = Mchm * sonicL[0] velTht = sonicL[1] print( 'velChm=%g ft/sec(%g m/s), velTht=%g ft/sec(%g m/s)'%(velChm, velChm*0.3048, velTht, velTht*0.3048 ) ) densityL = ispObj.get_Densities( Pc=Pc, MR=MR, eps=eps, frozen=frozen) densChm = densityL[0] densTht = densityL[1] print( 'densChm=%g lbm/cuft, densTht=%g lbm/cuft'%(densChm, densTht ) ) Dt = 2.0*Rt Dchm = Dt * fac_CR**0.5 print( 'Dchm=%g in(%g cm), Dt=%g in(%g cm)'%(Dchm, Dchm*2.54, Dt, Dt*2.54 ) ) Cpchm, viscchm, condchm, Prandtlchm = ispObj.get_Chamber_Transport( Pc=Pc, MR=MR, eps=eps, frozen=frozen) Cpt, visct, condt, Prandtlt = ispObj.get_Throat_Transport( Pc=Pc, MR=MR, eps=eps, frozen=frozen)
