| Value | Unit | Symbol | Description | |
| Various constants | 3.14 | - | pai | π = 3.14: Pi |
| 1.01E+05 | N/m2 | Pa | Pa = 1.013 × 105: Atmospheric pressure [N/m2] | |
| 1000 | kg/m3 | Dw | Dw: Density of water [kg/m3] | |
| 1.29 | kg/m3 | Dair | Dair: Air density at 15˚C 1 atm [kg/m3] | |
| 1.4 | γ | γ = 1.4: Specific heat ratio of air | ||
| 287.03 | J/kg·K | R | R = 287.03: Air gas constant [J/kg·K] | |
| 0.34 | - | C | C = 0.34: Drag coefficient of air resistance | |
| 0.528 | - | Kchoke | Kchoke = (2/γ + 1)γ/γ−1: Critical pressure coefficient | |
| Varieties of rocket | 6.30E−03 | m2 | S | S = π × (4.5 × 10−2)2: Rocket body sectional area [m2] |
| 0.165 | kg | Mb | Mb = 0.165: Rocket mass [kg] | |
| 0.18 | m | L | L: Guide rail length [m] | |
| 6.36E−05 | m2 | a | a = π × (4.5 × 10−3)2: Cross section of injection port [m2] | |
| 1.50E−03 | m3 | PVo | PVo = 1.5 × 10−3: Volume of fuel tank [m3] | |
| Initial condition | 5.07E+05 | N/m2 | Pstart | Tank air pressure at launch [N/m2] |
| 283.2 | K | Temp | Tank air temperature at launch [K] | |
| 6.23E+00 | kg/m3 | Dair_start | Tank air density at launch [kg/m3] | |
| 7.85E−01 | rad | KAstart | Launch angle [rad] (2π × θ/360˚) | |
| 0.5 | kg | Mw_start | Tank water mass at launch [kg] (at 10˚C) |