Unformatted text preview: 2 . Calculate the local Mach number and total temperature. 6. Show that for a perfect gas, M = u a o [1γ1 2 ( u a o ) 2 ]1 / 2 Then show that for Mach numbers much less than unity, this reduces to M = u a o [1 + γ1 4 ( u a o ) 2 ] 7. Air ±ows isentropically from atmosphere at a pressure of 1 atm through two di²erent ducts, each of uniform cross section. In ducts A and B, the static pressures are 85 × 10 3 N/m 2 and 36 × 10 3 N/m 2 , respectively. The atmospheric temperature is 15.0 deg. C. Using tables , Fnd the Mach numbers, static temperatures, and velocities in A and B. 8. Air ±ows isentropically from atmospheric conditions (p = 1 atm, T = 300 K) into a duct with a crosssectional area of 200 cm 2 . At one point in the duct, the Mach number is 1.6. Calculate the static pressure, velocity, static temperature at this location, along with the mass ±ow rate. 1...
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 Spring '11
 Dr.Edwards
 Fluid Dynamics, Thermodynamics, Aerodynamics, Mach number, Mach numbers

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