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1. A uniform supersonic flow at Mach 2.0, with static pressure of 75 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...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through a Prandtl-Meyer expansion wave/fan. Consider the gas to be calorically perfect Air with upstream properties as follows: M1 = 4, P = 20 kPa, T = 250 K. Find: 0-150 M2 (a) freestream Prandtl-Meyer function, Vi. (b) downstream Mach number, M2. (c) downstream static pressure, P2. (d) downstream static temperature, T2.
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...
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...
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...
Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted...
Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted by a plate at an angle of 10° with respect to the oncoming flow. An expansion fan is established at the edge of the plate, determine the pressure, temperature and Mach number behind the expansion fan.
1. Find the loss in stagnation pressure through a normal shock with an incoming flow at a Mach number of 2 and incoming...
1. Find the loss in stagnation pressure through a normal shock with an incoming flow at a Mach number of 2 and incoming flow stagnation pressure of 200 kPa(abs). In addition to the stagnation pressure downstream of the shock, also give the Mach number and (static) pressure downstream of the shock. DISCUSSION: Compare the "shock compression" (increase in STATIC pressure) obtained from the normal shock to the compression that would be obtained from an isentropic deceleration to the same Mach...
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...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it is flying through to be calorically perfect Air. The air-data system measures the following quantities: freestream static pressure is 6.5 kPa, Pitot pressure is 36.75 kPa, total temperature is 433 K. (a) freestream Mach number, M.. (b) freestream static temperature, T. (c) freestream velocity (air speed), U. 4. Supersonic gas enters a duct with a constant area at M - 2.5 at a pressure...
Problem 4 (15%) A supersonic wind tunnel operates with air at the total pressure Pt temperature...
Problem 4 (15%) A supersonic wind tunnel operates with air at the total pressure Pt temperature Te 420K, and Mach number M 2.0. 420kPa absolute, total a) (10%) Calculate the temperature and the pressure in the test section (where M 2.0 occurs). T1 = kPa (5%) if a normal shock wave occurs in the test section, calculate the temperature and pressure after the shock wave. b) kPa
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...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through a Prandtl-Meyer expansion wave/fan. Consider the gas to be calorically perfect Air with upstream properties as follows: M1 = 4, P = 20 kPa, T = 250 K. Find: 0-150 M2 (a) freestream Prandtl-Meyer function, Vi. (b) downstream Mach number, M2. (c) downstream static pressure, P2. (d) downstream static temperature, T2.
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...
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...
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...
Air at static conditions of 100kPa and 400K and a Mach number of 3.0 is diverted by a plate at an angle of 10° with respect to the oncoming flow. An expansion fan is established at the edge of the plate, determine the pressure, temperature and Mach number behind the expansion fan.
1. Find the loss in stagnation pressure through a normal shock with an incoming flow at a Mach number of 2 and incoming flow stagnation pressure of 200 kPa(abs). In addition to the stagnation pressure downstream of the shock, also give the Mach number and (static) pressure downstream of the shock. DISCUSSION: Compare the "shock compression" (increase in STATIC pressure) obtained from the normal shock to the compression that would be obtained from an isentropic deceleration to the same Mach...
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...
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it is flying through to be calorically perfect Air. The air-data system measures the following quantities: freestream static pressure is 6.5 kPa, Pitot pressure is 36.75 kPa, total temperature is 433 K. (a) freestream Mach number, M.. (b) freestream static temperature, T. (c) freestream velocity (air speed), U. 4. Supersonic gas enters a duct with a constant area at M - 2.5 at a pressure...
Problem 4 (15%) A supersonic wind tunnel operates with air at the total pressure Pt temperature Te 420K, and Mach number M 2.0. 420kPa absolute, total a) (10%) Calculate the temperature and the pressure in the test section (where M 2.0 occurs). T1 = kPa (5%) if a normal shock wave occurs in the test section, calculate the temperature and pressure after the shock wave. b) kPa
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