Homework Answers
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...
fluid dynamics: 4. (a) List the conditions that cause an oblique shock to form (b) A Mach 2.4 air flow at 450 K and...
fluid dynamics:
4. (a) List the conditions that cause an oblique shock to form (b) A Mach 2.4 air flow at 450 K and 1.9 bar is deflected (6) 15 by a standing oblique shock. Obtain the two possible shock angles (0) and identify the angles associated with the weak shock and the strong shock. 5 (c) Determine the conditions after the weak shock (i.e. calculate T,, p, and M2)
4. (a) List the conditions that cause an oblique shock...
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...
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...
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...
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....
please write your own answer! 3. Air flows in a converging-diverging nozzle is operating between the second and the thi...
please write your own answer!
3. Air flows in a converging-diverging nozzle is operating between the second and the third critical points as shown in figure below 40° IS where M, 2.35, T = 160K, p, = 0.7 bar and the receiver pressure is 1.0 bar (a) Compute the Mach number, temperature and the flow deflection in region 2 5 (b) Through which angle is the flow deflected as it passes though the next shock eave? (c)Determine the conditions in...
please write your own answer! 3. Air flows in a converging-diverging nozzle is operating between the second and the thi...
please write your own answer!
3. Air flows in a converging-diverging nozzle is operating between the second and the third critical points as shown in figure below 40° IS where M, 2.35, T = 160K, p, = 0.7 bar and the receiver pressure is 1.0 bar (a) Compute the Mach number, temperature and the flow deflection in region 2 5 (b) Through which angle is the flow deflected as it passes though the next shock eave? (c)Determine the conditions in...
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...
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
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...
fluid dynamics:
4. (a) List the conditions that cause an oblique shock to form (b) A Mach 2.4 air flow at 450 K and 1.9 bar is deflected (6) 15 by a standing oblique shock. Obtain the two possible shock angles (0) and identify the angles associated with the weak shock and the strong shock. 5 (c) Determine the conditions after the weak shock (i.e. calculate T,, p, and M2)
4. (a) List the conditions that cause an oblique shock...
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...
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...
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...
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....
please write your own answer!
3. Air flows in a converging-diverging nozzle is operating between the second and the third critical points as shown in figure below 40° IS where M, 2.35, T = 160K, p, = 0.7 bar and the receiver pressure is 1.0 bar (a) Compute the Mach number, temperature and the flow deflection in region 2 5 (b) Through which angle is the flow deflected as it passes though the next shock eave? (c)Determine the conditions in...
please write your own answer!
3. Air flows in a converging-diverging nozzle is operating between the second and the third critical points as shown in figure below 40° IS where M, 2.35, T = 160K, p, = 0.7 bar and the receiver pressure is 1.0 bar (a) Compute the Mach number, temperature and the flow deflection in region 2 5 (b) Through which angle is the flow deflected as it passes though the next shock eave? (c)Determine the conditions in...
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...
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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