Consider an oblique shock generated at a compression corner with a deflection angle
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Fundamentals of Aerodynamics
- Consider a convergent-divergent duct with exit and throat areas of 0.5 m^2 and 0.25 m^2, respectively. The inlet reservoir pressure is 1 atm and the exit static pressure is 0.6 atm. For this pressure ratio, the flow will be supersonic in a portion of the nozzle, terminating with a normal shock inside the nozzle. Calculate the local area ratio (A/A*) at which the shock is located inside the nozzle.arrow_forwardA jet of water from a nozzle is deflected through an angle θ = 60° from its original direction by a curved vane which it enters tangentially (see Fig. 5.5) without shock with a mean velocity C1 of 30 m s−1 and leaves with a mean velocity C2 of 25 m s−1. If the discharge A from the nozzle is 0.8 kg s−1, calculate the magnitude and direction of the resultant force on the vane if the vane is stationary.arrow_forwardAir at a stagnation temperature and pressure of 201 K and 6.895 x 105 N/m2, respectively, flows from a reservoir through a converging nozzle that exhausts into an atmosphere where the pressure is 1.014 x 105 N/m2. Calculate: a) the pressure in the nozzle exit plane, b) the minimum stagnation pressure for which the flow is chocked, c) the exit plane pressure if the stagnation pressure is reduced to 1.724 x 105 N/m2.arrow_forward
- Air flows through the supersonic nozzle . The inlet conditions are 7 kPa and 420°C. The nozzle exit diameter is adjusted such that the exiting velocity is 700 m/s. Calculate ( a ) the exit temperature, ( b )the mass flux, and ( c ) the exit diameter. Assume an adiabatic quasiequilibrium flowarrow_forwardA normal shock produced by an explosion propagate at a constant velocity of 450 m/s into still air of 100 kPa and 23 °C. The ratio of stagnation pressure upstream the shock to stagnation pressure of the gas flow behind the wave isarrow_forwardA double-acting cylinder has a plunger of 10 cm in diameter. The diameter ratio between the plunger and the stem is 5. This cylinder is connected to a compressed air network at the pressure of 2 MPa and performs 15 cycles per minute. Assuming a friction force equal to 10% of the theoretical one, calculate: a) The force exerted by the stem in the advance race and the one exerted in the return race. b) The stroke length if the air flow, measured under normal conditions, is 583 l/min. c) What would be the section of a single-acting cylinder, working with traction, that would provide the same flow?arrow_forward
- The air temperature is 288K and the pressure is 1 atm upstream of a shock wave; After the passing through the shock wave, the temperature of the air is 690K and the pressure is 8.656 atm. Calculate the change in a) enthalpy b) internal energy, and c) entropy across the wave. Assume R = 0.287 kJ/kg⋅K and ? = 1.4arrow_forwardA horizontal axis wind turbine with a 35-m diameter rotor is 40% efficient at 7.5 m/s winds and at 1 atm of pressure and 15° C. (a) How much power would it produce at these conditions? (b) What would the air density be on the peak of Mount Robson in the Rainbow Range which has an elevation of 3954 m at -8.5° C? (c) Determine the power the wind turbine would produce on the mountain with the same wind speed. Assume that the efficiency of the turbine is not affected by density and the coefficient of friction is the same at both altitudes. Is it beneficial to build the turbine on top of this mountain?arrow_forwardNozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air through a convergent-divergent nozzle. The stagnation temperature = 300K, stagnation pressure at the inlet = 107500Pa, static pressure at the exit=4400Pa, C1 is a constant = 0.1097 for calculating circular cross-sectional area of a convergent-divergent nozzle: A = C1 + x^2 and x (axial distance from the throat) =1m. γ = 1.4 and R=287. Calculate the mass flow rate of air through the nozzle. Thank You.arrow_forward
- Air flows through a constant cross-section conduit with Mack number Ma = 1 at 200 KPa pressure and 100°C temperature. State the necessary assumptions and calculate, (a) stagnation temperature (b) stagnation pressure, and (c) stagnation density.(d) With the specified inlet velocity a gas is flowing isentropically in the converging duct. At thethroat if we assume that the velocity is supersonic, how does the mass flow rate be affectedcompared to sonic velocity at the throat. How could supersonic velocity can be achieved in thiscase?arrow_forwardThe converging-diverging flow domain is shown in Figure 1. The inlet diameter is 0.2 m, the throat diameter is 0.15 m, and the outlet diameter is 0.24 m. The axial distance from the inlet to the throat is 0.30 m—the same as the axial distance from the throat to the outlet. At the inlet section, the stagnation pressure P0 is set to 220 kPa (absolute), while the stagnation temperature T0, at the inlet is set to 300 K.arrow_forwardAn aircraft is flying at supersonic speed. At a component of an aircraft where the flow is perpendicular, the density ratio is 5. Solve for: a.Mach Number Downstream b. Pressure Ratio c. Temperature Ratio d. Mach Number upstreamarrow_forward
- Principles of Heat Transfer (Activate Learning wi...Mechanical EngineeringISBN:9781305387102Author:Kreith, Frank; Manglik, Raj M.Publisher:Cengage Learning