A supersonic flow at
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- Gas flowing through a diverging nozzle has at inlet section a temperature of 20 °C, pressure 120 kN/m? and velocity 300 m/s. At the outlet of the nozzle the velocity has fallen to 100 m/s. Assuming an adiabatic flow, what is the values of outlet pressure, temperature, internal energy and specific enthalpy at outlet section. Take y = 1.333 and Cv= 0.86 kJ/kg K.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_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
- 85. Calculate the altitude of a supersonic airplane (v = 800 m-s1, T=-34 C°) when the time between seeing above observer and hearing is 9.9 sec.arrow_forwardQ2/ Starting with the differential form of the energy equation, show that the flow velocity increases with heat addition in subsonic Rayleigh flow, but decreases in supersonic Rayleigh flow.arrow_forward58. Find the height of a supersonic airplane (v = 670 m-s1, T = - 44 C°) when the time between seeing above observer and hearing is 8.8 sec.arrow_forward
- Good day. Here is my question (10) Consider a low-speed subsonic wind tunnel with a 12/1 contraction area ratio for the nozzle. If the flow in the test section is at a standard sea level conditions with a velocity of 50 m /s, calculate the height difference in a U-tube mercury manometer with one side connected to the nozzle inlet and the other to the test section. ρHg = 13.6 x 103 kg/ m^3.arrow_forwardConsider a low-speed open-circuit subsonic wind tunnel. The tunnel is turned on, and the pressure difference between the inlet (the settling chamber) and the test section is read as a height difference of 10 cm on a U-tube mercury manometer. (The density of liquid mercury is 1.36 × 104 kg/m3.) Assume that a Pitot tube is inserted into the test-section flow of the wind tunnel. The tunnel test section is completely sealed from the outside ambient pressure. Calculate the total pressure measured by the Pitot tube, assuming the static pressure at the tunnel inlet is atmospheric. Given that A2/A1 = 1/12. (Round the final answer to two decimal places.) The total pressure measured by the Pitot tube is × 105 N/m2.arrow_forwardUpstream of the throat of an isentropic converging-diverging nozzle at section (1), V₁ = 150 m/s, P1 = 100 kPa (abs), T₁ = 20°C. If the discharge flow is supersonic and the throat area is 0.10 m², determine the mass flowrate in kg/s for the flow of air. kg/s m = iarrow_forward
- Consider a circular cylinder in a hypersonic flow, with its axisperpendicular to the flow. Let φ be the angle measured between radiidrawn to the leading edge (the stagnation point) and to any arbitrary pointon the cylinder. The pressure coefficient distribution along the cylindricalsurface is given by Cp = 2 cos2 φ for 0 ≤ φ ≤ π/2 and 3π/2 ≤ φ ≤ 2πand Cp = 0 for π/2 ≤ φ ≤ 3π/2. Calculate the drag coefficient for thecylinder, based on projected frontal area of the cylinder.arrow_forward5. Airflow at Mach 2 passes through an oblique shock as shown and deflects 10°. A second oblique shock reflects from the solid wall. What is the pressure ratio (p3/p₁) across the two-shock system? Assume that there is no boundary layer near the wall, so the flow is uniform in each of the regions bounded by the shocks and that y = 1.4. Reflected oblique shock 10° M=2arrow_forwardA horizontal jet, with a density of 1097 kg/m and a diameter of 14.6 cm, is deflected upwards by a 90° bend. Calculate the force needed to keep the bend in place. The inflow has a uniform velocity v₁ = (1.8; 0; 0) m/s, and ambient pressure is 1.18 bar. The flow is non-viscous, the water jet leaves with a diameter of 10.4 cm, and the mass of the bend itself may be neglected. Both in- and outflow have a circular cross-section. Give your answer in 1 decimal accuracy. Y L. FI == sn N Fy = ___ N -arrow_forward
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