4.7 An incident shock wave with wave angle = 30° impinges on a straight wall. If the upstream flow properties are M₁ = 2.8, p₁ = 1 atm, and T₁ = 300 K, calculate the pressure, temperature, Mach number, and total pressure downstream of the reflected wave.

What is the minimum nozzle-diameter ratio De/D0 for which we can safely neglect compressibility effects if V0 = 10 m/s?

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)?

The flow just upstream of a normal shock wave is given by p1 = 1 atm,T1 = 288 K, and M1 = 2.6. Calculate the following properties justdownstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change inentropy across the shock.

An air tank with a nozzle, has a pressure of twice the standard sea level pressure and density of 2.45 kg/m³. Outside the converging-diverging nozzle, the pressure corresponds to an altitude of 3km and designed to have a mach number of 1.0 and 1.8 at the throat and exit, respectively. The area at the throat is 0.15 square meters. Calculate: a) the temperature and speed of sound in the tank. b) pressure and density at the throat c) mass flow rate at the exit.

are 3000 ft/s and 500°R, respectively Calculate the Mach number M and the characteristic Mach number M* at this point 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; P1 M2, u2, Po,, and T %3! = 1 atm, and p, = 1 23 kg/m Calculate the downstream values of P2, 02 35 Consider a Pitot static tube mounted on the pose of an experımental airplane A

Air with Mach number of 2.5, To 300 K and P. = 2 bar passes through the steps shown in figure. Determine: (1) The fan angle of the expansion wave (2) M, Ts and P4. M₁ = 2.5 T₂ = 300 Po 2 bar M₁ May M 20° 10

3.4. Consider a normal shock wave in air The upstream conditions are given by M1 = 3; 1 23 kg/m' Calculate the downstream values of p2, T,, 1 atm, and p1 M2, u2, Po,, and T, P1 P24 02 Dis

Air flows isentropically through a duct as shown in the figure below. For the conditions shown, find the Mach number at both stations 1 and 2 and the flowrate. The diameter is not necessarily constant. Ma₁ (1) D₁ = 0.15 m V₁ = 40 m/s P1 = 4 atm abs. Ma₁ = Ma₂ = i m₁ = M. kg/s Ma₂ (2 T₂ = 225 K P2 = 2 atm abs.

At a point in the flow over an F-15 high-performance fighter airplane, the density,temperature and Mach number are 1 kg/m3, 240 Kelvin, and Mach 1.6.(a) At this point, calculate T0, ρ0, p0, a0, T ∗, a∗, p∗ and the flow velocity.(b) Calculate M ∗1 and, using the Prandtl relation, calculate M ∗2 and u2 after a normalshock.