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- A 1:7 scale model simulates the operation of alarge turbine that is to generate 200 kW with a flowrate of 1.5 m3/s.What flow rate should be used inthe model, and what power output is expected?(a) Water at the same temperature is used in bothmodel and prototype.(b) The model water is at 25°C and the prototypewater is at 10°C.Example 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848Determine 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.
- 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 H₂OAir at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance from the entrance to the point at which the hydrodynamic boundary layers meet.derive an expression for the mass flowrate of air for a C-D nozzle arrangement operating in choked flow conditions. Hint: start with the fact that: mmax = p* A*V * show all your steps. upload your answer here.
- A flow with Mach number M1 = 2 and pressure p1 = 1 atm is turned away from itself twice,first through an angle of 10 deg and then through a second angle of 20 deg. Compute the Machnumber and the static pressure downstream of the second turn. Then, suppose that the original flow(M1 = 2 and p1 = 1 atm) is turned away from itself through a single turn of 30 deg. Compute theMach number and static pressure downstream of this turn, and show that the values are the sameas for the first flow with two turns totaling 30 deg.3solve question 21, please, dynamicsA jet engine on a test stand directs a stream of hot exhaust gasses against a vemcal wall. All of the exhaust gas leaving the wall after impact is in the y-z plane (ie no "x" direction velocity). The mass rate is 200 kg/s and the velocity is 400 m/s. (Note that the density and viscosity are not relevant) What is the force on the wall (include direction)?
- The following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image. Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed Aircraft lift-off speed 155 knots Max take-off gross weight 220 tonnes Wing planform area (S) 358 m Wing CL (t/o flaps deployed, a = 0) 1.1 Wing span 53.18 m Oswald efficiency factor, e 0.7 KGE = CD(IGE) / Co(OGE) 0.4 Co sum (fuselage, wing, tailplane and nacelle) 0.015 Co for undercarriage 0.021 Co for flaps at taking-off setting 0.0073 Coefficient of rolling friction, u 0.02 Engine thrust (assumed constant) 310 kN per engine It may be assumed that 1knot = 0.51444 m/s It may be assumed that 1knot = 0.51444 m/sThe Drag Polar Equation of an General Aviation Aircraft in clean configuration can be written as: C2 Cp = 0.0270+ %3D 32.787 Its weight is 2300 lb and the wing area is 155ft?, Calculate the (L/D)max and the Minimum Thrust Required (Unaccelerated Level flight and Sea level Condition)In the field of air pollution control, one often needs to sample the quality of a moving airstream. In such measurements a sampling probe is aligned with the flow as sketched in Fig. A suction pump draws air through the probe at volume flow rate V· as sketched. For accurate sampling, the air speed through the probe should be the same as that of the airstream (isokinetic sampling). However, if the applied suction is too large, as sketched in Fig, the air speed through the probe is greater than that of the airstream (super iso kinetic sampling). For simplicity consider a two-dimensional case in which the sampling probe height is h = 4.58 mm and its width is W = 39.5 mm. The values of the stream function corresponding to the lower and upper dividing streamlines are ?l = 0.093 m2/s and ?u = 0.150 m2/s, respectively. Calculate the volume flow rate through the probe (in units of m3/s) and the average speed of the air sucked through the probe.