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An airplane uses a pitot-static tube as a velocimeter. The measurements, with their uncertainties, are a static temperature of
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- An airplane uses a pitot-static tube as a velocimeter. Themeasurements, with their uncertainties, are a static temperatureof (-11 ± 3)°C, a static pressure of 60 ± 2 kPa,and a pressure difference (po 2 ps) = 3200 ± 60 Pa.(a) Estimate the airplane’s velocity and its uncertainty.(b) Is a compressibility correction needed?arrow_forwardDescribe physically what the “speed of sound” represents.What kind of pressure changes occur in air sound wavesduring ordinary conversation?arrow_forward2. A fan discharges 265 cu.m/min of air through a duct of 92 cm in diameter against a static pressure of 0.022 m of water. The fluid density is 995 kg/cu.m., the air temperature is 29°C and the barometric pressure reading is 730 mm Hg. If the power input to the fan is measured 3.5 hp, what are the total and static fan efficiencies?arrow_forward
- Water fl owing in a smooth 6-cm-diameter pipe entersa venturi contraction with a throat diameter of 3 cm.Upstream pressure is 120 kPa. If cavitation occurs in thethroat at a fl ow rate of 155 gal/min, what is the estimatedfl uid vapor pressure, assuming ideal frictionless fl ow?( a ) 6 kPa, ( b ) 12 kPa, ( c ) 24 kPa, ( d ) 31 kPa, ( e ) 52 kPaarrow_forwardA bicycle tire is fi lled with air at an absolute pressure of169.12 kPa, and the temperature inside is 30.0 °C. Supposethe valve breaks, and the air starts to exhaust out of the tireinto the atmosphere (pa = 100 kPa absolute and Ta =20.0 °C). The valve exit is 2.00 mm in diameter and is thesmallest cross-sectional area of the entire system. Frictionallosses can be ignored here; one-dimensional isentropicflow is a reasonable assumption. (a) Find the Machnumber, velocity, and temperature at the exit plane of thevalve (initially). (b) Find the initial mass flow rate out ofthe tire. (c) Estimate the velocity at the exit plane using theincompressible Bernoulli equation. How well does thisestimate agree with the “exact” answer of part (a)? Explain.arrow_forwardAssume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2(2116 lb/ft2), respectively. Consider the flow field over a circular cylinder mounted perpendicular tothe flow in the test section of a low-speed subsonic wind tunnel. Atstandard sea level conditions, if the flow velocity at some region of theflow field exceeds about 250 mi/h, compressibility begins to have an effectin that region. Calculate the velocity of the flow in the test section of thewind tunnel above which compressibility effects begin to become important, i.e., above which we cannot accurately assume totallyincompressible flow over the cylinder for the wind tunnel tests.arrow_forward
- 5. Consider a Pitot probe in high-speed flow.(c) You are flying through air at static p∞ = 0.8 atm [abs]. Your velocimeter broke,but you are still receiving the following direct stagnation pressure readings (atm[abs]) from the Pitot probe mounted on your aircraft’s noise: i) 3.152 ii) 1.357 iii) 38.428 iv) 0.8 Find the freestream Mach number corresponding to each of the pressure readings. (d) If we are to believe reading (iv), can we step out of the aircraft safely? Why?arrow_forwardIf Reynolds number relate the inertial and viscous forces, which of the following relates the inertial andgravitational forces?A. Froude NumberB. Weber NumberC. Galileo NumberD. Eotvos Numberarrow_forwardA normal shock wave was formed on the surface of a supersonic aircraft at a velocity of 1,600 m/s into still atmospheric air at standard seal level conditions. Calculate: a) M₁ b) M₂ c) P₂ d) T₂ e) V₂arrow_forward
- A blimp approximates a 4:1 spheroid that is 196 ft long. Itis powered by two 150 hp ducted fans. Estimate the maximumspeed attainable, in mi/h, at an altitude of 8200 ft.arrow_forward1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Calculate cp, cv, e, and h fora. The stagnation point of a high-speed missile are 934 ◦R and 7.8 atm, respectively.b. Air at standard sea level conditionsarrow_forwardNitrogen gas under a pressure pn = 15 psig is used for pumping kerosene at 25°C (density = 816 kg/m3, viscosity = 1.81 cP) through an elevation increase of 6 m. If there is an effective length of 45 m of nominal 2-in. schedule No. 40 pipe (commercial steel) between the two tanks, what is the flow rate of kerosene? Neglect exit kinetic-energy effects.arrow_forward
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