assume standard atmosphere conditions at surface (101.3 kPa). A lightweight UAV
ID: 1819874 • Letter: A
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assume standard atmosphere conditions at surface (101.3 kPa).
A lightweight UAV is designed to fly in the upper stratosphere to collect atmosphere data. The nominal altitude of aircraft is z = 35 km at a velocity of 80 kph (kilometers/hour) Determine the pressure, density .and temperature that the aircraft will encounter at that altitude using the standard atmosphere shown, Note that R= 287 J.kg - K for air and g = 9.81 m/s2. To test the UAV design. a 1/10th scale model is put in a wind tunnel The critical dimensionless groupings for dynamics similitude are Reynolds number (Re = rhoUL/ mu)and Mach number . Wind tunnel temperature is fixed at 25 degree C. and the equation for air viscosity as a function of temperature is : A = 1.46 Times 10-6 kg/m.s.K1/2 S=110.3K Assume the ratio of specific heat for air is gamma = 1.4 and is a constant. To adjust conditions in the wind tunnel, we can change: the air pressure and the (low velocity. What wind tunnel pressure and flow velocity are necessary to achieve dynamic similitude for the given conditions?Explanation / Answer
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