At the seashore, you observe a supersonic aircraft moving overhead at an elevation of 2500 m, you hear the plane 5.5 seconds after it passes directly overhead. Using a nominal air temperature of 15°C, estimate the Mach number and speed of the aircraft.
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- 85. Calculate the altitude of a supersonic airplane (v = 800 m-s1, T=-34 C°) when the time between seeing above observer and hearing is 9.9 sec.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.An aircraft is flying at 440 km/hr at 3 km on a standard day. What is the aircraft Mach Number?
- . Determine the aircraft Mach no. flies with the same Mach no. at elevations of 8700m (T=-55 C°) and 11700 m (T = – 62 C°), if the aircraft flies 15% slower at 11700 m altitude.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.Determine the lift coefficient of a supersonic aerofoil, approximated by a flat plate. It is flying at Ma 3.4 at an angle of attack of 7°. Assume the fluid to be air as a perfect gas with k=1.4.
- 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 thisAn engineer is designing a subsonic wind tunnel. The test section is to have a cross-sectional area of 4 m2 and an airspeed of 60 m/s. The air density is 1.2 kg/m3. The area of the tunnel exit is 10 m2. The head loss through the tunnel is given by hL=0.025VT2/2g, where VT is the airspeed in the test section. Calculate the power needed to operate the wind tunnel. Hint: Assume negligible energy loss for the flow approaching the tunnel in region A, and assume atmospheric pressure at the outlet section of the tunnel. Assume α = 1.0 at all locations.2. A particle is moving in air at sea level where the temperature is 18°C. The two disturbance spheres created by the particle at points A and B are shown in the figure below. Determine the Mach no. and velocity of the particle. (Hint: For different time intervals choose the first sphere i.e. the bigger) Ans: 0.5, 171 m-s?. 9m 3m Particle <
- Consider a typical air flow around a cruising jetliner at 10km altitude. The speed is now 810 km/h, while the ambient conditions are 0.414 kg/m³ , 0.261 atm and -50°C. At the stagnation point, the temperature rises over by 25°C, while the density and pressure changes by more than 30% and 45 % respectively. Classify the following situations as compressible/incompressible flowThe instrument fairing on an aircraft is shown below, consisting of a forward ramp at30◦, a horizontal section, and a rear ramp at 25◦. During a flight in air at Mach 5.5,the static pressure is 42.6 kPa and the static temperature is 250 K. An oblique shockforms at the turn of the forward ramp, two expansion fans form at the front and rear ofthe horizontal section, and a second oblique shock forms at the turn of the rear ramp. (a) Calculate the Mach numbers and pressures at regions 2, 3, 4, and 5. (b) Determine stagnation pressure ratio p05/p01. (c) Tabulate the angles of all oblique shocks waves leading/trailing expansion waves relative to horizontal (not relative to flow angle). Gamma = 1.4, R=287 J/kgK PLEASE SHOW ALL WORKA moving point disturbance travels at a supersonic speed. It creates two spheres one at time (t) and the next one after (8t) time interval, 36 m ahead. Assuming the medium to be standard sea level atmosphere with 20°C, calculate the Mach number and velocity of the object and the Mach angle of the cone created by the disturbance. V It =3m 36m R=12m i+ St