Value | Unit | Symbol | Description | |
Various constants | 3.14 | - | pai | π = 3.14: Pi |
1.01E+05 | N/m^{2} | P_{a} | P_{a} = 1.013 × 10^{5}: Atmospheric pressure [N/m^{2}] | |
1000 | kg/m^{3} | D_{w} | D_{w}: Density of water [kg/m^{3}] | |
1.29 | kg/m^{3} | D_{air} | D_{air}: Air density at 15˚C 1 atm [kg/m^{3}] | |
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 | - | K_{choke} | K_{choke} = (2/γ + 1)^{γ}^{/γ−1}: Critical pressure coefficient | |
Varieties of rocket | 6.30E−03 | m^{2} | S | S = π × (4.5 × 10^{−2})^{2}: Rocket body sectional area [m^{2}] |
0.165 | kg | M_{b} | M_{b} = 0.165: Rocket mass [kg] | |
0.18 | m | L | L: Guide rail length [m] | |
6.36E−05 | m^{2} | a | a = π × (4.5 × 10^{−3})^{2}: Cross section of injection port [m^{2}] | |
1.50E−03 | m^{3} | P_{Vo} | P_{Vo} = 1.5 × 10^{−3}: Volume of fuel tank [m^{3}] | |
Initial condition | 5.07E+05 | N/m^{2} | P_{start} | Tank air pressure at launch [N/m^{2}] |
283.2 | K | T_{emp} | Tank air temperature at launch [K] | |
6.23E+00 | kg/m^{3} | D_{air_start} | Tank air density at launch [kg/m^{3}] | |
7.85E−01 | rad | KA_{start} | Launch angle [rad] (2π × θ/360˚) | |
0.5 | kg | M_{w_start} | Tank water mass at launch [kg] (at 10˚C) |