To plot: the mass flow parameter.
Answer to Problem 148P
Explanation of Solution
Given:
Mach number
Calculation:
Equation is given by
The graph for the above values is given below:
Conclusion:
Therefore, for the values Ma and k are plotted but only one value of
Want to see more full solutions like this?
Chapter 12 Solutions
FLUID MECHANICS FUNDAMENTALS+APPS
- The Mach number of an aircraft that travels with a speed of 260 m/s in air at 25° C while it undergoes the compressibility effect will be: (Use speed of sound in air at 0° C: 331 m/s) Select one: a. M = 0.69 b. M= 0.70 c. M= 0.75arrow_forwardWhat is the Mach Number of an air with a velocity of 250 m/s, at a temperature at 2800 meters?arrow_forward(b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the duct and friction within air can be neglected. The diameter of the duct is 10cm and the air temperature and pressure at the inlet are T₁ 450 K and P₁ = 200 kPa. If the Mach number at the exit is Ma2 determine the rate of heat transfer and the pressure difference across the duct. The constant pressure specific heat of air is cp = 1.005 kJ/kg-K. The gas constant of air is R = 0.287 kJ/kg-K and assume k = 1.4. -arrow_forward
- Determine the critical mach number according to linear theory(hand written)arrow_forwardAt a point in the flow over an F-15 high-performance fighter airplane, the density,temperature and Mach number are 1 kg/m3, 240 Kelvin, and Mach 1.6.(a) At this point, calculate T0, ρ0, p0, a0, T ∗, a∗, p∗ and the flow velocity.(b) Calculate M ∗1 and, using the Prandtl relation, calculate M ∗2 and u2 after a normalshock.arrow_forwardFind the velocity of bullet fired in standard air if the Mach angle is 45°. Take R=287.14 J/kg K and k = 1.4 for air. Assume temperature as 27°Carrow_forward
- Q4//B/ Heat is removed from airflow in a constant-area duct, if flow enters at Mach 2.20, T1= 310 K, and p1= 120 kPa. Determine exit Mach number and the amount of heat removing from the duct if the static temperature at exit section is 255 K. justify your solution for M2arrow_forwardIn a wind tunnel air enters with a velocity of 200kmph. The static pressure and temperature of the air at the inlet of the tunnel is 110kPa and 27°C respectively. Determine Mach number, stagnation temperature, stagnation pressure and the stagnation density on a test model installed in the wind tunnel. The size of the tunnel is given as 1m x1m square cross-section. Determine the mass flow rate of the air. For air assume R=287J/kgK ; γ=1.4.arrow_forwardLooking for correct solutionarrow_forward
- Determine the critical mach number according to linear theory((clear hand written plzzzz))arrow_forwardFind the expression for the ratio of the stagnation pressure after a shock wave to the static pressure before the shock wave as a function of k and the Mach number upstream of the shock wave Ma1arrow_forwardA supersonic aircraft flies with a velocity lower by 39 m-s at 7800 m elevation, (T = - 54 C° at 7800 m) and (T = - 57 C° at 8800 m, M = 2), determine the difference between Mach no.s.arrow_forward
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY