100 lbf Aerojet HiPAT R-4D

RocketIsp version 0.1.8 Friday, Dec 04, 2020 at 04:32PM
      N2O4/N2H4
IspVac     = 324.093 sec
MRcore     = 1.26
MRthruster = 0.882
Rt         = 0.356745 in
At         = 0.399821 in**2
Pc         = 137 psia
Fvac       = 100 lbf
Plot
Plot
Plot
Geometry
Input
Parameter = Value Alt Value Description
cham_conv_deg = 30.00 deg half angle of conical convergent section
CR = 2.5 chamber contraction ratio (Ainj / Athroat)
eps = 375 nozzle area ratio (Aexit / Athroat)
LchamberInp = None in user input value of chamber length (will override all other entries)
LchmMin = 1.000 in 2.540 cm
0.083 ft
minimum chamber length (will override LchmOvrDt)
LchmOvrDt = 3 ratio of chamber length to throat diameter (Lcham / Dthrt)
LnozInp = None in user input nozzle length (will override pcentBell)
pcentBell = 80 nozzle percent bell (Lnoz / L_15deg_cone)
RchmConv = 1 radius of curvature at start of convergent section (Rconv / Rthrt)
RdwnThroat = 1 radius of curvature just downstream of throat (Rdownstream / Rthrt)
Rthrt = 0.357 in 0.906 cm
0.030 ft
throat radius
RupThroat = 1.5 radius of curvature just upstream of throat (Rupstream / Rthrt)
Output
Parameter = Value Alt Value Description
Ainj = 1.000 in**2 6.449 cm**2 area of injector
At = 0.400 in**2 2.579 cm**2 throat area
Dexit = 13.817 in 35.094 cm
1.151 ft
nozzle exit diameter
Dinj = 1.128 in 2.865 cm
0.094 ft
diameter of injector
Dthrt = 0.713 in 1.812 cm
0.059 ft
throat diameter
entrance_angle = 39.79 deg nozzle initial expansion angle
exit_angle = 7.65 deg nozzle exit angle
Lcham_conv = 0.598 in 1.519 cm
0.050 ft
length of convergent section of chamber
Lcham_cyl = 1.542 in 3.918 cm
0.129 ft
length of cylindrical section of chamber
Lnoz = 19.561 in 49.684 cm
1.630 ft
nozzle length
Ltotal = 21.701 in 55.121 cm
1.808 ft
nozzle + chamber length
Rinj = 0.564 in 1.433 cm
0.047 ft
radius of injector
Vcham = 1.9 in**3 31.9 cm**3 approximate chamber volume
N2O4/N2H4 Core Stream Tube
Input
Parameter = Value Alt Value Description
adjCstarODE = 1 multiplier on NASA CEA code value of cstar ODE (default is 1.0)
adjIspIdeal = 1 multiplier on NASA CEA code value of Isp ODE (default is 1.0)
CdThroat = 0.985275 Cd of throat (RocketThruster object may override)
(MLP fit)
fuelName = N2H4 name of fuel (e.g. MMH, LH2)
ignore_noz_sep = 0 flag to force nozzle flow separation to be ignored (USE WITH CAUTION)
MRcore = 1.26 mixture ratio of core flow (ox flow rate / fuel flow rate)
oxName = N2O4 name of oxidizer (e.g. N2O4, LOX)
Pamb = 0.00 psia 0.00 MPa
0.00 atm
0.00 bar
ambient pressure (for example sea level is 14.7 psia)
Pc = 137.0 psia 0.94 MPa
9.32 atm
9.45 bar
chamber pressure
Output
Parameter = Value Alt Value Description
CfAmbDel = 1.82564 delivered ambient thrust coefficient
CfVacDel = 1.82564 delivered vacuum thrust coefficient
CfVacIdeal = 2.01252 ideal vacuum thrust coefficient
cstarERE = 5729.7 ft/s 1746.4 m/s delivered core cstar
cstarODE = 5787.6 ft/s 1764.1 m/s core ideal cstar
FvacBarrier = 40.8 lbf 181.4 N vacuum thrust due to barrier stream tube
FvacCore = 59.2 lbf 263.5 N vacuum thrust due to core stream tube
FvacTotal = 100.0 lbf 444.8 N total vacuum thrust
gammaChm = 1.13912 core gas ratio of specific heats (Cp/Cv)
IspDel = 324.09 sec 3178.27 N-sec/kg
3.18 km/sec
<=== thruster delivered vacuum Isp ===>
IspDel_core = 335.21 sec 3287.30 N-sec/kg
3.29 km/sec
delivered Isp of core stream tube
IspODE = 362.02 sec 3550.20 N-sec/kg
3.55 km/sec
core one dimensional equilibrium Isp
IspODF = 337.52 sec 3309.90 N-sec/kg
3.31 km/sec
core frozen Isp
IspODK = 346.44 sec 3397.42 N-sec/kg
3.40 km/sec
core one dimensional kinetic Isp
MRthruster = 0.882 total thruster mixture ratio')
MWchm = 20.222 g/gmole core gas molecular weight
Pexit = 0.0124 psia 0.00 MPa
0.00 atm
0.00 bar
nozzle exit pressure
TcODE = 5521.3 degR 3067.4 degK
2794.2 degC
5061.6 degF
ideal core gas temperature
wdotFl = 0.164 lbm/s 0.074 kg/s total fuel flow rate
wdotOx = 0.145 lbm/s 0.066 kg/s total oxidizer flow rate
wdotTot = 0.309 lbm/s 0.140 kg/s total propellant flow rate (ox+fuel)
At Injector Face
Parameter = Value Alt Value Description
wdotFl_cInit = 0.115 lbm/s 0.052 kg/s initial core fuel flow rate (before any entrainment)
wdotFlFFC = 0.049 lbm/s 0.022 kg/s fuel film coolant flow rate injected at perimeter
wdotTot_cInit = 0.259 lbm/s 0.118 kg/s initial core total flow rate (before any entrainment)
After Entrainment
Parameter = Value Alt Value Description
wdotFl_b = 0.086 lbm/s 0.039 kg/s barrier fuel flow rate (FFC + entrained)
wdotFl_c = 0.078 lbm/s 0.035 kg/s final core fuel flow rate (injected - entrained)
wdotOx_b = 0.046 lbm/s 0.021 kg/s barrier oxidizer flow rate (all entrained)
wdotOx_c = 0.099 lbm/s 0.045 kg/s final core oxidizer flow rate (injected - entrained)
wdotTot_b = 0.132 lbm/s 0.060 kg/s total barrier propellant flow rate (includes entrained)
wdotTot_c = 0.177 lbm/s 0.080 kg/s total final core propellant flow rate (injected - entrained)
Efficiencies
Output
Parameter = Value Description
Isp = 0.89524 Overall Isp Efficiency
Noz = 0.93530 Nozzle Efficiency
ERE = 0.99000 (constant) Energy Release Efficiency of Chamber
FFC = 0.96683 (barrier calc) Fuel Film Cooling Efficiency of Chamber
Nozzle
Parameter = Value Description
Div = 0.99403 (simple fit eps=375, %bell=80) Divergence Efficiency of Nozzle
Kin = 0.95697 (MLP fit) Kinetic Efficiency of Nozzle
BL = 0.98323 (MLP fit) Boundary Layer Efficiency of Nozzle
Ignored Efficiencies
        TP: Two Phase Efficiency of Nozzle
Barrier Stream Tube
Input
Parameter = Value Description
ko = 0.035 entrainment constant (typical value is 0.035, range from 0.03 to 0.06)
pcentFFC = 30 percent fuel film cooling ( FFC flowrate / total fuel flowrate)
Output
Parameter = Value Alt Value Description
cstarERE_b = 5490.6 ft/s 1673.5 m/s delivered cstar
cstarODE_b = 5546.1 ft/s 1690.5 m/s ideal equilibrium cstar
fracKin_b = 0.0628378 fraction of kinetic completion in barrier
IspDel_b = 309.20 sec 3032.17 N-sec/kg
3.03 km/sec
delivered vacuum barrier Isp
IspODE_b = 321.837 sec. ideal equilibrium barrier Isp
IspODF_b = 319.40 sec 3132.24 N-sec/kg
3.13 km/sec
ideal frozen barrier Isp
IspODK_b = 319.55 sec 3133.74 N-sec/kg
3.13 km/sec
vacuum kinetic Isp of barrier
MRbarrier = 0.537454 barrier mixture ratio
MRwall = 0.215753 mixture ratio at wall
TcODE_b = 4153.2 degR 2307.3 degK
2034.2 degC
3693.5 degF
average ideal ODE temperature of barrier gas
Twallgas = 2774.3 degR 1541.3 degK
1268.1 degC
2314.6 degF
temperature of gas at wall
WentrOvWcool = 1.68107 ratio of entrained flow rate to FFC flow rate