Theoretical Rocket Performance

Internal gas dynamics of liquid rocket engines and solid rocket motors with equilibrium flow and frozen flow is discussed. In evaluating the rocket performance under equilibrium flow, the application of the three key derivatives [,, and cp] is explained. The performance parameters (characteristic velocity c∗, thrust coefficient CF, and specific impulse Isp) under the equilibrium flow and the frozen flow are discussed to show that the parameters assume different values for the two flows. To demonstrate the application of the knowledge gained, the design analysis on the internal ballistics and engine-envelope determination of proven engines, such as Space Shuttle Main Engine (SSME), is carried out. Also problems with answers are added on the design analyses of some proven engines: R-1E Marquardt, Mitsubishi LE-5B, and Vulcain.