y = 1.4 M = 3.0 % $ = 40° 0 ts=20°
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- write MATLAB scripts to solve the following. Give MATLAB CODE : Que: Air flowing at Mach 2.5 with a pressure of 60 kPa and a temperature of 2020°C passes over a wedge which turns the flow through an angle of 44 leading to the generation of oblique shock waves One of the oblique shock waves impinges on a flat wall, which is parallel to the flow upstream of the wedge and is. " from it Find the pressure and velocity behind the reflected shock wave GIVE MATLAB CODE TO SOLVE ?A pump running at 1,440 rpm has to support a load of 10 kN. Journal diameter is 130 mm. Design a suitable Finite hydrodynamic journal bearing (L/D=1) with radial clearance of 0.065mm. The inlet oil film temperature is 45oC. Calculate the bearing characteristics and the required heat dissipation. Design , Pleas solve it quiqly thank you for your helpProblem-2 For the turbulent incompressible boundary layer, the velocity profile is given as u/Ue, y = y/8, Ue and d are boundary-layer edge velocity where, u = and boundary layer thickness, respectively. Using momentum integral equation, prove that: 8/x = 0.383/Re,/5 8% /x = 0.0479/Re/5 and 0/x = 0.0372/Re/5
- Q4-Q6: A device is used to cool hot copper spheres of diameter 5 mm from an average temperature of 200C to 50C by letting them fall in air at 25°C and latm. Use drag coefficient C, = 0.4 and Whitaker correlation in your calculations. Assume the spheres fall at their terminal velocities during the process. Q4 improve the accuracy? Iteration is not required. ) Determine the terminal velocity of a sphere. Is the use of C, = 0.4 appropriate? If not, how toProblem 2 An unconfined supersonic flow passes over the contoured wall shown below. The wall segment AB is a 30° arc of a circle of radius R and wall segment is a 30° arc of a circle of radius R. Calculate the wall static pressures at B and C. Mo. = 2.0 P., = 1 bar == A B R 30° 30° R C(Q)A pump running at 1,440 rpm has to support a load of 10 kN. Journal diameter is 130 mm. Design a suitable Finite hydrodynamic journal bearing (L/D=1) with radial clearance of 0.065mm. The inlet oil film temperature is 450C. Calculate the bearing characteristics and the required heat dissipation. *
- 2. In an undistur bed airstream, where the pressure is 14.7 in' and the the velocity n G00 "/secwhat are the velocity, density 10/in? temperaturej 519 'R, and speed of sound where the pressure il 13.9 temperatureDetermine the velocity required for take off for an aircraft with the following characteristics.Aircraft mass: 7200 kgWingspan: 15 mWing shape: rectangularWing chord length: 1.8 mWing airfoil: NACA 4415Wing angle of attack: 7× 0.5 + 5 degreesHint: Check NACA charts for required parameters.solve question 21, please, dynamics
- The shock waves on a vehicle in supersonic flight cause a component ofdrag called supersonic wave drag Dw. Define the wave-drag coefficient asCD,w = Dw/q∞S, where S is a suitable reference area for the body. Insupersonic flight, the flow is governed in part by its thermodynamicproperties, given by the specific heats at constant pressure cp and atconstant volume cv. Define the ratio cp/cv ≡ γ . Using Buckingham’spi theorem, show that CD,w = f (M∞, γ ). Neglect the influence of friction.A steam generator generates flue gas at an average temperature of 260 C inside a Chimney. The theoretical draft is 0.5 kPa and the ambient condition of the air is 21 C and 100 kPa. Assume the coefficient velocity to be 0.30 and the molecular weight of the flue gas is 32. For air-fuel ratio requirements per second of 15, calculate: a. The diameter of the Chimney, meter b. The theoretical draft, cm H₂OCalculate the Reynolds numbers at the root chord location for the following aircraft. Assume that the density and dynamic viscosity of air at sea level are 0.002378 slug/ft’ and 3.737 x 107 slug/(ft•s): (a) A DC-3 with a wing root chord length 15.25 ft flying at 250 ft/s at sea level. (b) An F-22 with a wing root chord length 21.5 ft flying at 920 ft/s at sea level.