γ
R
Chamber Pressure
Chamber Temperature
Nozzle Throat
Diameter
Efficiency
Combustion
Nozzle
Exhaust Pressure
& Equivalent Altitude
Ambient Pressure
& Equivalent Altitude
F
Thrust
N
ISP
I
SP
(Specific Impulse)
s
mdot
Mass Flow Rate
kg/s
LN
Nozzle Length
m
DE
Exit Diameter
m
ARATIO
Expansion Ratio
ME
Exit Mach
PePc
Pressure Ratio
VE
Exit Velocity
m/s
TE
Exit Temperature
°K
CSTAR
Characteristic Velocity (C*)
m/s
ISP2
I
SP
(Specific Impulse)
s
FTotal
Total Thrust
N
TWR
TWR
DV
∆V
km/s
J/kg.K
500
100
MPa
25
1
°K
5000
1000
m
1
0.001
%
%
98
85
km
kPa
space
sea-lvl
km
kPa
space
sea-lvl
Number of Engines
Engine Unit Mass
Fuel Mass
Payload Mass
 
                                   
Click a starting point on the Delta-V map to predict the range of paths achievable by the above rocket engine and vehicle configuration, travelling between some of the nearer parts of the Solar System.
Default start: Earth.

Note: This Delta-V budget map does not take rocket-staging into account, nor does it facilitate boosters (hence why some of the presets fail to lift off from earth when in reality they are able to).

The calculation also freezes the above engine ISP at its design ambient pressure/altitude, so atmospheres of destinations/origins don't alter the engine performance like they would in real life.
It also assumes that at each subsequent waypoint after the original launch point, the vehicle has a sufficient thrust to weight ratio (TWR) to lift off again.