7. Air at 10 km above sea level, initially travelling at supersonic speed is decelerated thru a normal shock wave. The deceleration caused a velocity of 1,600 Kph after the wave. Calculate the following: a. Velocity and Mach number before the wave b. P, ???, T, and V? after the wave. Ans. M? = 8.31, V? = 2,487.52 m/s, P? = 2,116,510.84 Pa, ???? = 2.300 kg/m3, T? = 3,203.22 K, Va? = 1,134.77 m/s
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\[ V_2 = 1600 \, \text{Kph} \times \frac{1000 \, \text{m}}{1 \, \text{Km}} \times \frac{1 \, \text{h}}{3600 \, \text{s}} = 444.44 \, \text{m/s} \] Show more…
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A blast wave propagates outward from an explosion. At large radii, curvature is small and the wave may be treated as a strong normal shock. (The pressure and temperature rise associated with the blast wave decrease as the wave travels outward.) At one instant, a blast wave front travels at $M=1.60$ with respect to undisturbed air at standard conditions. Find (a) the speed of the air behind the blast wave with respect to the wave and (b) the speed of the air behind the blast wave as seen by an observer on the ground. Draw a $T s$ diagram for the process as seen by an observer on the wave, indicating static and stagnation state points and property values.
Air approaches a normal shock at $V_{1}=900 \mathrm{m} / \mathrm{s}, p_{1}=50$ $\mathrm{kPa},$ and $T_{1}=220 \mathrm{K} .$ What are the velocity and pressure after the shock? What would the velocity and pressure be if the flow were decelerated isentropically to the same Mach number?
1. A very weak pressure wave, i.e., a sound wave, across which the pressure rise is 30 Pa moves through air which has a temperature of 30°C and a pressure of 101 kPa. Find the density change, the temperature change, and the velocity change across this wave. 2. An airplane is traveling at 1500 km/h at an altitude where the temperature is -60°C. What is the Mach at which the airplane is flying? 3. Calculate the speed of sound at 288 K in hydrogen, helium, and nitrogen. Under what conditions will the speed of sound in hydrogen be equal to that of helium? 4. A normal shock wave occurs in an airflow at a point where the velocity is 680 m/s, the static pressure is 80 kPa, and the static temperature is 60°C. Find the velocity, static pressure, and static temperature downstream of the shock. 5. A perfect gas flows through a stationary normal shock. The gas velocity decreases from 480 m/s to 160 m/s through the shock. If the pressure and the density upstream of the shock are 62 kPa and 1.5 kg/m³, find the pressure and density downstream of the shock and the specific heat ratio of the gas. 6. Complete the steps between these two equations. (γ + 1) M₂² / 2 + (γ - 1) M₂² = [(γ + 1) M₁² / 2 + (γ - 1) M₁²]⁻¹ (3.50) Solving Eq. (3.50) for M₂²: M₂² = 1 + [(γ - 1) / 2] M₁² / γM₁² - (γ - 1) / 2 (3.51)
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