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

Q3- Consider a fluid flow in round tube of length 1m and diameter 5mm. Classify the flow as laminar and turbulent and calculate the entrance length for (a) air (50 °C) with a speed of 12 m/s. (b) water (17.5°C) and mass flow rate of 8 g/s. (Vair = 1.79x105 m²/s and water 1.14x10-5 N.s/m²).

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.

) 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.

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.

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?

plz answer both.

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