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A First Course on Aerodynamics by A. Roy

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By A. Roy

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Since the expansion process is isentropic, the From the above equation the value of properties in region 2 can be calculated using isentropic relations. 2 A supersonic flow at Mach number=2, temperature=300K, pressure=1atm and density= approaches a compression corner. An attached oblique shock with wave angle=45° is formed at the corner. Find the normal Mach numbers upstream and downstream of the shock. 4. , . 41 atm, which is far less than that for a normal shock. Therefore it reiterates the fact that an oblique shock is a weaker shock than normal shock.

Efficient flying vehicles in transonic Mach number regime use thin airfoil and swept wing design in order to reduce wave drag and increase critical Mach number. Another two design features which are used in all contemporary transonic flying vehicles are ‘area rule’ and ‘supercritical airfoil’. The reader is encouraged to explore these issues through further reading. 6 Hypersonic flow Hypersonic aerodynamics is associated with flows at high Mach numbers, usually higher than 5. Like transonic flow, hypersonic flow is also highly non linear in nature.

41 atm, which is far less than that for a normal shock. Therefore it reiterates the fact that an oblique shock is a weaker shock than normal shock. 5 Linearised Theory: Compressible flow past thin airfoil When an irrotational, inviscid, compressible flow is considered the continuity, momentum and energy equations simplify to a single governing equation in one dependent variable, namely, the velocity potential Φ, the gradient of which gives the velocity vector. 49) ‘a’ is variable. From energy equation assuming that stagnation enthalpy is constant in the flow an expression for ‘a’ is obtained which is given below where a 0= γRT0 .

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