-A Mach No. (0.6) airplane flies at an altitude of (10000) meters where the atmospheric temperature is (4.4 C). Calculate the airplane velocity.
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- Calculate the ratio of kinetic energy to internal energy at a point in an airflow where the Mach number is: (a) M = 2, and (b) M = 20.Starting from the basic principles, drive an expression to compute the lift coefficient when the free stream Mach number equals (0.8)What is the Mach Number of an aircraft flying at 3000 ft with 450 m/s?What is the aspect ratio of a tapered wing with span of 8m and a planform area of 20 m^2
- An air compressor increases the pressure (Pout > Pin) and the density (?out > ?in) of the air passing through it. For the case in which the outlet and inlet diameters are equal (Dout = Din), how does average air speed change across the compressor? In particular, is Vout less than, equal to, or greater than Vin? Explain.In your own words, write a summary of the differences between incompressible flow, subsonic flow, and supersonic flow.On March 16, 1990, an Air Force SR-71 set a new continental speedrecord, averaging a velocity of 2112 mi/h at an altitude of 80,000 ft.Calculate the temperature (in degrees Fahrenheit) at a stagnation point onthe vehicle.
- Air at 20°C and 1 atm flow past the flat plate in Fig.under laminar conditions. There are two equally spacedpitot stagnation tubes, each placed 2 mm from the wall.The manometer fluid is water at 20°C. If U = 15 m/s andL = 50 cm, determine the values of the manometer readingsh1 and h2, in mm.5. At 30000ft, estimate the magnitude of transonic drag rise. Using this estimate, calculate the maximum velocity of the airplane at this altitude. Assume drag-divergence Mach number of 0.82 and d(D/D₁)/dM = 14.3 where D₁=1750lb is drag at Mach number 0.9 and D₂ = 4250lb at Mach number 1. 6 Estimate maximum range at 30000€ Also calculate the flight speed to obtain thisThrust is required to propel an airplane at a fi nite forwardvelocity. Does this imply an energy loss to the system?Explain the concepts of thrust and drag in terms of the fi rstlaw of thermodynamics.
- (a) The maximum speed achieved by the X-15A-2 rocket-powered research craft was 6630 ft/s at 99,000 ft. Assuming standard day conditions, whatwas its Mach number?(b) An SR-71 is traveling at Mach 3.2 in standard day 80,000-ft conditions.What is its velocity in nautical miles per hour?a balloon is 4 m in diameter and contains helium at 125 kpa and 15°c. balloon material and payload weigh 200 n, not including the helium. estimate (a) the terminal ascent velocity in sea-level standard air, (b) the final standard altitude (neglecting winds) at which the balloon will come to rest, and (c) the minimum diameter (< 4 m) for which the balloon will just barely begin to rise in sea-level standard air.Consider a flat plate at α = 20◦ in a Mach 20 freestream. Using straightnewtonian theory, calculate the lift- and wave-drag coefficients. Comparethese results with exact shock-expansion theory.