2. Energy Equation on static parameters

3. Ddefinition of gas-dynamic functions and their purpose

They are dimensionless functions of the deceleration parameters and the criteria for the velocity regime of the flow M or $\lambda$

M-Mach number

$\lambda$-reduced speed

5. Basic kinematic relation for a direct jump

Total pressure will either be constant or decrease, which represent reversible and irreversible respectively.

6. The law of reversal of influence for thermal influence

a-speed of sound.

7. Darcy's formula

待解决 (local loss

$$ l = \xi_{fr} \frac l d \frac {W^2} 2 $$

15. Thrust formula

19. Momentum equation in gas-dynamic form

待办：回头推一下

20. Equation for calculating exergy losses from irreversibility

这里少了一个$\nabla$

22. Purpose of the nozzle.

25. Weisbach formula.

$$ l_{locali} = \xi_{i} \frac {W_i^2} {2} $$

27. Formula for calculating braking pressure loss in a forward shock.

疑似：

29. Integral energy equation in thermal form for an elementary trickle

31. The equation of momentum in gas-dynamic form, written in terms of total pressure.

给了

35. Continuity equation based on braking parameters

39and41. changing the state of gas

修正：

$$ P = (G_a + G_g) w_c - G_a w_p + (p_c - p_H)F_c , \text{for turbine} \\ P = G w_c + (p_c - p_H)F_c, \text{for rocket engine} $$

42. Critical parameters

待解决

43. Bernoulli's equation in differential form

45. Bernoulli's equation for an incompressible fluid in integral form

46. Flow coefficient for nozzle

48. Energy equation energetically isolated system

Let the left hand side equal zero.

49. Energy euqation total parameter

$$ e = C_p T^* $$

54. Differential energy equation in mechanical form

58. Flow equation based on static parameters

Total parameters:

$$ G = m \frac {p^* q(\lambda) F} {\sqrt{T^*}}, \text{where } m \text{ is called flow rate constant} $$