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Air flowing with a Mach number of 2 with a pressure of 80 kPa and a...
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...
7.8. Air at 800°R and 15 psia is flowing at a Mach number of M =...
7.8. Air at 800°R and 15 psia is flowing at a Mach number of M = 1.8 and is deflected through a 15° angle. The directional change is accompanied by an oblique shock. (a) What are the possible shock angles? (b) For each shock angle, compute the temperature and pressure after the shock.
Can you please do this question correctly,thanks!! 183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T,...
Can you please do this question correctly,thanks!!
183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T, which are defined in the table below 185 186 Value Design Data Unit 187 188 Upstream static pressure (P) 96 kPa 189 Upstream static temperature (T) 265 CK 190 Upstream mach number (M) 2.55 WATCH 191 Wedge half-angle (e) 18 UNITS 192 193 Your answers 194 a) Find the wedge...
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 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 number, and post shock pressure for this flow
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...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. Ti = °C P1 = kPa m V = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa
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....
3. A normal shock wave exists in Mach 2 stream of air having temperature and pressure...
3. A normal shock wave exists in Mach 2 stream of air having temperature and pressure of 45°F and 30 psia, respectively. Calculate the Mach number, pressure, and temperature downstream of the shock wave.
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a...
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex corner. Determine the downstream Mach number M,, Fan angle Мi Mа 10°
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T, = °C P1 = kPa V1 = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. p2 = kPa m V2 =
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...
7.8. Air at 800°R and 15 psia is flowing at a Mach number of M = 1.8 and is deflected through a 15° angle. The directional change is accompanied by an oblique shock. (a) What are the possible shock angles? (b) For each shock angle, compute the temperature and pressure after the shock.
Can you please do this question correctly,thanks!!
183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T, which are defined in the table below 185 186 Value Design Data Unit 187 188 Upstream static pressure (P) 96 kPa 189 Upstream static temperature (T) 265 CK 190 Upstream mach number (M) 2.55 WATCH 191 Wedge half-angle (e) 18 UNITS 192 193 Your answers 194 a) Find the wedge...
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 number, and post shock pressure for this flow
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...
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. Ti = °C P1 = kPa m V = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. P2 = kPa
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....
3. A normal shock wave exists in Mach 2 stream of air having temperature and pressure of 45°F and 30 psia, respectively. Calculate the Mach number, pressure, and temperature downstream of the shock wave.
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex corner. Determine the downstream Mach number M,, Fan angle Мi Mа 10°
1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 kPa and a temperature oi 250 К, ехрands aгound a 10 degrees pressure p2, temperature T,, and the fan angle. convex...
Problem 3 (30%) Dry air flows from a reservoir in which the temperature is 200°C and pressure is 600 kPa absolute. a) (20%) Assuming isentropic flow, calculate the temperature, pressure, and velocity when the Mach number is 2.1. T, = °C P1 = kPa V1 = b) (10%) A normal shock wave forms at the location where the Mach number is 2.1. Calculate the pressure and velocity after the shock wave. p2 = kPa m V2 =
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