By A. Roy
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Extra resources for A First Course on Aerodynamics
Example text
The above equation states that the internal energy increase across a shock is equal to the average pressure across the shock times the reduction in specific volume. , 1 atmospheric pressure, which is approximately and respectively. Calculate Mach number, velocity, static temperature, static pressure, stagnation temperature and stagnation pressure downstream of the shock. 4 . 333) = 540K p 0, 2 p2 γ γ − 1 2 γ −1 M2 = 1 + 2 It is interesting to find out the loss in stagnation pressure across the shock.
From the geometry of the problem, the expansion angle ∆q can be obtained as where q1 and q2 are the inclinations of the surfaces in regions 1 and 2 respectively. The expansion angle is defined in terms of the change of Prandtl-Meyer function as follows ν ( M 2 ) is obtained. 46) can be used to iteratively calculate M . 2 Alternatively, Prandtl-Meyer function tables can be used to obtain M 2 . Since the expansion process is isentropic, the From the above equation the value of properties in region 2 can be calculated using isentropic relations.
If chemical reactions get completed within this short transit time, they are said to be equilibrium chemical reactions, if not, they are said to be non equilibrium chemical reactions. The equilibrium or non-equilibrium nature of chemical reactions can alter the flow characteristics. Very often hypersonic vehicles have a blunt nose. Since the qmis very large near the nose, close to 90º, a curved detached shock called as a bow shock is formed. The portion of the shock near the nose of the body is normal.