Air enters from ambient atmosphere into a level duct of uniform cross-sectional area 0.2 m2 at a flow rate of 2.0 m3/s and density of 1.2 kg/m3. The entry shock loss factor is 1.0 and the resistance of the duct per meter length is 1.0 Ns2/m8. The static pressure measured at a distance of 20 m from the duct entrance in Pa, is

For axial flow through a circular tube, the Reynolds numberfor the transition to turbulence is approximately 2300  based on the diameter and average velocity. Ifd= 5 cm and the fl uid is kerosene at 20 ° C, fi nd the volumeflow rate in m 3 /h that causes transition.

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 75 mm-diameter orifice is on the verticalside of a closed tank. The tank rests on a flat groundand the orifice is 0.5 m above the ground. Filled withfour fluids with air on the topmost portion that is undera pressure of 15 KPa, and the rest of specific gravities of0.80, 1.0, and 1.50, respectively, the jet hits the groundat a horizontal distance of 3.75 m. If the liquids have thesame thickness, and the power lost in the system is 233watts, determine the following:(a) The initial discharge in L/s if C=0.63.(b) The thickness of each liquid in m.(c) The coefficient of contraction.

1. when , the flow is accelerates if the cross sectional area is increases ( a) M 1 (c) M =1 2. If the sonic conditions does occur in the duct it will occur at the duct maximum area(T/F) 3. For laminar zone the velocity profile will be (a) Linear (b) (b) Parabolic (c) (c) Logarithmic (d) (d)none of above 4. The thickness of boundary layer decreases as distance from leading edge increase(T/F) 5. The main property that effects a boundary layer is... (a) Temperature (b) pressure (c) viscosity (d) surface tention.

For the following situations of steady flow, calculate the Reynold's Number and determine whether flow is laminar or turbulent, or in the transition regionAir at 2 atm pressure and 180°F flowing at 50 ft/s in a 12-in. duct.

What is the critical value of the pressure coefficient for an airplane flying at 170m/s in air at 2 deg C?

A long fi xed tube with a rounded nose, aligned with anoncoming fl ow, can be used to measure velocity. Measurementsare made of the pressure at (1) the front nose and(2) a hole in the side of the tube further along, where thepressure nearly equals stream pressure.( a ) Make a sketch of this device and show how the velocityis calculated. ( b ) For a particular sea-level airfl ow, the differencebetween nose pressure and side pressure is 1.5 lbf/in 2 .What is the air velocity, in mi/h?

Answer the following: 1-The principle of wind tunnel design involves divergent nozzle intake, Explain the reasons behind that. 2-Most of the pressure reading over the upper side surface are negative, Explain. 3-The change in angle of attack can be noticed from reading of the pitot tube. Explain. 4-The fluctuation in pitot tube reading during velocity distribution experiment is due to

Jet water in pipe with diameter equal to 50 moving to velocity 30 divided into two branches with (0.75Q) and the other with (0.25Q) recpectively and Un equal diameter compnte value of force compenents on the plane