In your own words, write a summary of the differences between incompressible flow, subsonic flow, and supersonic flow.
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In your own words, write a summary of the differences between incompressible flow, subsonic flow, and supersonic flow.
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- Consider a cone at zero angle of attack in a hypersonic flow. (Hypersonic flow is very high-speed flow, generally defined as any flow above a Mach number of 5.) The half-angle of the cone is θc, as shown inthe figure. An approximate expression for the pressure coefficient on the surface of ahypersonic body is given by the newtonian sine-squared law : Cp = 2 sin2 θcNote that Cp, hence, p, is constant along the inclined surface of the cone. Along the base of the body, we assume that p = p∞. Neglecting the effect of friction, obtain an expression for the drag coefficient of the cone, where CD is based on the area of the base Sb.With the aid of diagrams, explain what are Mach waves and how they are formed. From your understanding, how can the speed of a fighter aircraft model inside the wind tunnel can be estimatedby observing the Mach wave angle using optical measurements?(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?
- Consider an airplane flying at a velocity of 250 m/s. Calculate its Mach number if it is flying at a standard altitude of (a) sea level, (b) 5 km, (c) 10 km.(0 The flow in a hard-disk drive at P=1 atm & T=25 °C. (i) Flow over airfoils on wind turbines. (i) Supersonic flight at 10 km from the ground. Which of the following flows can be treated as a continuum? (a) All four (i, ii, ii, lv) (b) i, ii, I (c) II, iI, iv (d) i, ii, iv (iv) Flow in a gas-turbine engine w/P= 30 atm & T = 2,000 KConsider the flow over a circular cylinder; the incompressible flow oversuch a cylinder . Consider also the flow over a sphere; the incompressible flow over a sphere .The subsonic compressible flow over both the cylinder and the sphere isqualitatively similar but quantitatively different from their incompressiblecounterparts. Indeed, because of the “bluntness” of these bodies, theircritical Mach numbers are relatively low. In particular: For a cylinder: Mcr = 0.404 For a sphere: Mcr = 0.57Explain on a physical basis why the sphere has a higher Mcr than thecylinder.
- A normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?A flow is said to be supersonic, if the (a) If the velocity of flow is very high (b) Mach number is between 1 and 6 (c) Mach number is more than 6 (d) If the discharge is difficult to measureA piston moves along a tube containing air at an initial sound speed of 330 m/s. When the piston velocity is 250 m/s, it drives a shock wave which propagates at a velocity of 500 m/s. When the piston velocity is 100 m/s, it drives a shock at 400 m/s. Use the hypersonic equivalence principle to calculate the shock angles (in degrees) on a flat plate: At an incidence of 6 degrees and a Mach number of 7.2
- At 300°C and 1 atm, estimate the speed of sound of(a) nitrogen, (b) hydrogen, (c) helium, (d ) steam, and(e) 238UF6 (k≈ 1.06).Discuss the significance of Reynolds number in pressurized flow analysis ?On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?