Q2: Helium, at To = 400 K, enters a nozzle isentropically. At section 1, where A1 = 0.1 m2, a pitot-static arrangement (see Fig. Q2) measures stagnation pressure of 150 kPa and static pressure of 123 kPa. Estimate (a) M1; (b) Tị; (c) mass flow; and (d) A*. Take y = 1.66 and R = 2077 J/(kg-K). Air at 100 K Mercury Ans. (a) 0.5; (b) 370 K; (c) 9.03 kg/s; and (d) 0.0756 m².

Q2: Helium, at To = 400 K, enters a nozzle isentropically. At section 1, where A1 = 0.1 m2, a pitot-static arrangement (see Fig. Q2) measures stagnation pressure of 150 kPa and static pressure of 123 kPa. Estimate (a) M1; (b) Tị; (c) mass flow; and (d) A*. Take y = 1.66 and R = 2077 J/(kg-K). Air at 100 K Mercury Ans. (a) 0.5; (b) 370 K; (c) 9.03 kg/s; and (d) 0.0756 m².

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Consider a normal shock wave at sea level with the density ratio, p2/p1 = 2.67. What %3D are the pressure, density, temperature, velocity and Mach number downstream of the wave?
Air flows steadily from a tank through the pipe inFig. . There is a converging nozzle on the end. Ifthe mass flow is 3 kg/s and the nozzle is choked, estimate(a) the Mach number at section 1 and (b) the pressureinside the tank.
section If the back pressure is low enough and the throat is sonic, the Mach number is more than I in a/an during flow in a convergent-divergent nozzle. 1. diverging X2. converging X 3. entry X 4. throat
(a) A pitot tube indicates a pressure of 265 kPa in an airstream in which the temperature is 10°C and the local Mach number is 1.5. Find the static pressure in the airstream. (b) In another problem, a normal shock wave occurs in air at a point where the stagnation temperature is 300°C and the velocity is 700 m/s. The stagnation pressure is 700 kPa. Under this situation do the following: (i) Draw a diagram and label all flow conditions. (ii) Evaluate the Mach numbers, static and stagnation pressures, static and stagnation temperatures before and after the normal shock. Give reasons to justify your answers.
None
The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic speeds at theexit, where p 2 = 8 kPa and T 2 = 240 K. At the throat, p 1=284 kPa, T 1 = 665 K, and V 1 = 517 m/s. For steadycompressible fl ow of an ideal gas, estimate ( a ) the mass fl owin kg/h, ( b ) the velocity V 2 , and ( c ) the Mach number Ma 2 .
Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 60.0 kPa (abs), T1 = 27°C, Vị = 486 m/s. At a downstream section 2, p2 = 78.8 kPa (abs). Determine: a. Mach number, Maz b. sketch geometry of the duct
A turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to that through a convergent-divergent de Laval nozzle with a normal shock at the nozzle exit. Just upstream of the shock, the exit Mach number Me = 1.09, the absolute static pressure pe = 280 kPa, the static temperature Te = 586 K, the ratio of specific heats of the combustion productsk = 1.35, and the constant pressure specific heat capacity Cp = 1027 J-kg "K-1. Assuming the combustion products are constant property ideal gasses, determine the density of the combustion products pp after the shock. State your answer in kg m to two decimal places and enter the numerical value only.
(6) The coefficient of discharge 1 point for a real nozzle (Theoretical mass flux= 639.8 kgs-1m-2, To= 510 K, Theoretical exit pressure= 67 kPa, Actual exit Mach no. =2.02) * 0.88 0.89 0.90 0.92
Air at pressure and temperature of 200 kPa, 373.2 K flows through a duct at 270m/s. The gas constant and specific heat ratio of air are 0.287 kJ/kg.k and 1.4respectively.(i) Show that the flow is compressible fluid flow.(ii) Determine stagnation pressure, stagnation temperature and stagnationdensity.
(5) (a) Air flows adiabatically through a duct. At point 1 the velocity is 240 m/s, with T₁ = 300 K and P=150 kPa. Compute (a) To1, (b) Po1, (c) Po1, (d) Mal, (e) Vmax, and (f) V*.