APPENDIX 3
SUMMARY OF KEY EQUATIONS FOR IDEAL CHEMICAL ROCKETS
| Parameter | Equations | Equation Numbers |
Average exhaust velocity,  (m/sec or ft/sec) (assume that  ) |
 |
2–15 |
When  ,  |
||
 |
3–16 | |
 with  |
3–15 | |
Effective exhaust velocity,  (m/sec or ft/sec) |
 |
3–32, 3–33 |
 |
2–15 | |
Thrust,  (N or lbf) |
 |
2–16, 4–9 |
 |
3–31 | |
 |
2–13 | |
 |
2–6 | |
| Characteristic velocity, c* (m/sec or ft/sec) |  |
3–32 |
 |
3–32 | |
 |
3–32, 3–33 | |
Thrust coefficient,  (dimensionless) |
 |
3–31, 3–32 |
 |
||
 |
3–30 | |
| Total impulse |  |
2–1, 2–2, 2–5 |
| Specific impulse, Is (sec) |  |
2–16, 3–33 |
 |
2–5 | |
 |
2–15 | |
 |
2–4, 2–5 | |
| Propellant mass fraction, (dimensionless) |  |
2–8, 2–9 |
 |
4–4 | |
Mass ratio of vehicle or stage,  (dimensionless) |
 |
2–7, 2–10 |
 |
||
 |
2–10 | |
Vehicle velocity increase in gravity‐free vacuum,  (m/sec or ft/sec) (assume that  ) |
 |
4–6 |
 |
4–5, 4–6 | |
 |
||
Propellant mass flow rate,  (kg/sec or lb/sec) |
 |
3–3 |
 |
3–24 | |
 |
2–16, 3–32 | |
 |
3–24 | |
Mach number,  (dimensionless) |
 |
3–11 |
At throat,  and  |
||
Nozzle area ratio,  |
 |
3–19 |
 |
3–14 | |
| Isentropic flow relationships for stagnation and free‐stream conditions |  |
3–7 |
 |
||
Satellite velocity,  , in circular orbit (m/sec or ft/sec) |
 |
4.26 |
Escape velocity,  (m/sec or ft/sec) |
 |
4.25 |
Liquid propellant engine mixture ratio  and propellant flow  |
 |
6.1 |
 |
6.2 | |
 |
6.4 | |
 |
6.3 | |
Average density  for (or average specific gravity) |
 |
7.2 |
Characteristic chamber length  |
 |
8.9 |
Solid propellant mass flow rate  |
 |
12–1 |
Solid propellant burning rate  |
 |
12–5 |
Ratio of burning area  to throat area  |
 |
12–4 |
| Temperature sensitivity of burning rate at constant pressure |  |
12–8 |
| Temperature sensitivity of pressure at constant K |  |
12–9 |
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