In Problem 11.8, the critical Mach number for a circular cylinder is given as
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- For a hotshot wind tunnel with T=50o0k and P=100 MPa. Calculate and plot Mach number as a function of ratio A/At for the choked nozzle of the tunnel for 1) air in thermochemical equilibrium and 2) air with chemical composition and all internal energies except for translational.arrow_forwardThe Born–Oppenheimer principle [1] is often said to be a prerequisite for the concept of a PES. Yet the idea of a PES [2] predates the Born–Oppenheimer principle (1927), Discussarrow_forwardExample 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848arrow_forward
- (b) Water boils at 95° C in a particular hill station. Estimate the approximate altitude (above the mean sea level) of the hill station, assuming that the atmosphere is isothermal at 25°C. At mean sea level, the pressure is 1 bar and water boils at 100°C with AHV=2256.94 kJ kg".arrow_forwardDerive an expression for the expansion coefficient of a perfect gas. Also derive an expression for the isothermal compressibility of a perfect gas.arrow_forward1-A projectile is fired into air in which the pressure is 340 kPa and the density is 4.5 kg/m3. It can be observed the Mach cone is originated from the projectile with a total angle of 20°. What is the speed of the projectile with respect to air?arrow_forward
- (b) An experimental balloon filled with helium is equipped with meteorological instruments is released to the atmosphere from sea level. Measurement data was analysed to derive the linear temperature lapse rate up to high altitudes above sea level. The lapse rate was found to be equal to 0.0065 K/m. Estimate the altitude of the balloon above sea level when the atmospheric pressure is equal to 60 kPa. Atmospheric temperature and pressure at sea level may be assumed to be equal to 15°C and 101 kPa. Characteristic gas constant is 287J/kgK.arrow_forwardWhich of the following statement is FALSE? A During fluid flow through many devices such as nozzles, diffusers, and turbine blade passages, flow quantities vary primarily in the flow direction only B) For an ideal gas, temperature decreases with increase in velocity. (C) Mach number depends on the speed ofsound, which depends on the state of the fluid. (D) In a converging nozzle, the velocity of the gas stream will never exceed the sonic velocity, though in a converging- diverging nozzle supersonic velocities may be obtained in the diverging section (E) In adiabatic compressible flow in a conduit of constant crosssection, the Mach number can exceed 1.0arrow_forward3.1. At a given point in the high-speed flow over an airplane wing, the local Mach number, pressure and temperature are 07, 09 atm, and 250 K, respectively Calculate the values of p,, T, p*, T*, and a* at this pointarrow_forward
- A symmetrical wedge-shaped object is decelerating during its travel initially still air. At a Mach number of 3, weak shocks at an angle of 40 degrees to the direction of travel are observed at the leading edge. Determine the Mach number at which the shock will detach. An accurate graphical solution is acceptable but must be accompanied by a sketch illustrating the solution method. Please provide drawing please. TY. I need the illustration.arrow_forward3. Consider a vehicle moving at a velocity of 1,000 mps through air and hydrogen. The specific gas constant of hydrogen is 4,157 ???−?⁄. Assume T = 300 K. a. Calculate the Mach number of the vehicle in air. b. Calculate the Mach number of the vehicle in hydrogen.arrow_forwardThe propagation of disturbances from a point source that results in an oblique shock wave can be visualized in Figure Q2(b). From the diagram, derive the equation that relates Mach angle with the local Mach number.arrow_forward
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