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A supersonic airfoil moves through air at 80kPa and -10°C with a Mach number of 2.0. The leading edge of the airfoil deflects the air at an angle of e the weak oblique shock angle, post shock Mach nu...
A supersonic flow of air with Mach number of M1=2.8 is deflected towards itself by 16o. What is the Mach number M2 behind the a weak oblique shock?
A supersonic flow of air with Mach number of M1=2.8 is deflected towards itself by 16o. What is the Mach number M2 behind the a weak oblique shock?
Air at Ma 2.0 and p 10 psia is forced to turn through 10° by a ramp at the body surface. A weak oblique shock is formed...
Air at Ma 2.0 and p 10 psia is forced to turn through 10° by a ramp at the body surface. A weak oblique shock is formed. The 10° deflection resulted in a final Mach number of 1.641 and a pressure ratio of 1.707. When the flow is made to turn through 5, the final Mach number is slightly higher, and the final pressure is slightly lower. Ma2 Ma 2.0 P 10 lbf/in 10° True False O O
Air at...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a temperature of 30°C passes over a component of an aircraft that can be modeled as a wedge with an included angle of 8° that is aligned with the flow. The flow is turned through an angle of 4°, leading to the generation of an oblique shock wave. Find after the oblique shock: a) the pressure b) the temperature. c) the Mach number after the...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number M1 = 2.5, and the pressure is pı = 50,000 N/m². The half-angle of the spike centerbody is 10°, as shown. For a particular mass flow through the engine, it happens that there is an oblique shock at a, and a normal shock wave standing at b. Before entering the second shock wave, the fluid expands through a Prandtl-Meyer turn, as the skech indicates....
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static...
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static pressure, pi, and static temperature, Ti, as specified in the table below, encounters a corner with a turning angle ore Determine the angle of the oblique shock, ?, the angle of the reflected wave, q, the Mach numbers M2 and M, and the downstream static pressure Ps and static temperature Ty Mi P1 M3 P3 T3 Design Data Value Unit Mach number (M) Static...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angl...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angles, θ¡et and θaf, at the leading and trailing edges, as defined in the figure and given in the table below. The airfoil operates at an angle of attack, α, and it is moving through air at a supersonic speed, M. The atmospheric temperature and pressure far upstream of the airfoil are T and p as specified in the table The various flow regions are...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. A...
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
Air at Ma 2.0 and p 10 psia is forced to turn through 10° by a ramp at the body surface. A weak oblique shock is formed. The 10° deflection resulted in a final Mach number of 1.641 and a pressure ratio of 1.707. When the flow is made to turn through 5, the final Mach number is slightly higher, and the final pressure is slightly lower. Ma2 Ma 2.0 P 10 lbf/in 10° True False O O
Air at...
Air flowing with a Mach number of 2 with a pressure of 80 kPa and a temperature of 30°C passes over a component of an aircraft that can be modeled as a wedge with an included angle of 8° that is aligned with the flow. The flow is turned through an angle of 4°, leading to the generation of an oblique shock wave. Find after the oblique shock: a) the pressure b) the temperature. c) the Mach number after the...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number M1 = 2.5, and the pressure is pı = 50,000 N/m². The half-angle of the spike centerbody is 10°, as shown. For a particular mass flow through the engine, it happens that there is an oblique shock at a, and a normal shock wave standing at b. Before entering the second shock wave, the fluid expands through a Prandtl-Meyer turn, as the skech indicates....
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static pressure, pi, and static temperature, Ti, as specified in the table below, encounters a corner with a turning angle ore Determine the angle of the oblique shock, ?, the angle of the reflected wave, q, the Mach numbers M2 and M, and the downstream static pressure Ps and static temperature Ty Mi P1 M3 P3 T3 Design Data Value Unit Mach number (M) Static...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angles, θ¡et and θaf, at the leading and trailing edges, as defined in the figure and given in the table below. The airfoil operates at an angle of attack, α, and it is moving through air at a supersonic speed, M. The atmospheric temperature and pressure far upstream of the airfoil are T and p as specified in the table The various flow regions are...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
Normal Shock Nozzle Exit (4, -6 cm? Back pressure Air from a reservoir at 350 K and 500 kPa, flows through a converging-diverging nozzle. The throat area is 3 cm- and the exit area is 6 cm. A normal shock appears, for which the downstream (region 2) Mach number (M2) is 0.6405. Reservoir Throat (A = 3 cm (a) What is the Mach number (M]) upstream of the shock? 350K, 500 kPa (abs) (b) What is the area where the...
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
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