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adiabatic angle of attack assumption calculated compressible fluid cone angle conical coordinate conical flow constant of integration control plane coordinate angle corresponding Mach number corresponding value deflection angle density ratio dependent variables derivation differential equation energy conservation energy equation enthalpy entropy change equation 16 equation 22 expansion shock expressed Figure 11 flow direction free stream Mach functions of Mach given Mach number heat addition Hence isentropic flow Mach number ahead Mach wave mass conservation relation normal shock number and deflection oblique shock theory obtained Plane Shock plane symmetric flow plotted in Figure point function point of heat pressure and density problem rate of mass region through control relation is plotted resultant velocity shock wave angle simply solution sonic point speed of sound stagnation point stagnation pressure ratio stagnation temperature stream Mach number streamline curve streamline direction streamtube subsonic supersonic tained by isentropic Taylor series Taylor-Maccoll theory tion written