Problem 4 – Consider the isentropic flow over an airfoil. The freestream conditionscorrespond to a standard altitude of 10,000 ft and M, = 0.82. At a given point on theairfoil, M = 1.0. Calculate P and T at this point.

Answered: Image /qna-images/answer/733eed62-1e22-47b9-841c-c8ba90b9caf9.jpg

Answered: Problem 4 – Consider the isentropic…

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.55P

See similar textbooks

Similar questions

For a given airfoil, the critical Mach number is 0.8. Calculate the value ofp/p∞ at the minimum pressure point when M∞ = 0.8.
True or False: Flow over conventional airfoils are highly viscous at lower angles of attack
An airfoil is in a freestream where p.(assigned altitude)atm, p(density) (assigned altitude) kg/m3, and V 980 m/s. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic flow, calculate the velocity at that point. assigned altitude 36.22km
Consider the isentropic flow over an airfoil. The freestream conditionscorrespond to a standard altitude of 10,000 ft and M∞ = 0.82. At a givenpoint on the airfoil, M = 1.0. Calculate p and T at this point.
Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area of 2 m2 and a test-section cross-sectional area of 0.5 m2. The pressure in the test section is 1 atm. Assume constant density equal to standard sea level density, calculate the pressure (in Pa) required in the reservoir necessary to achieve a flow velocity of 40 m/s in the test section.
The Boeing 747 has a wingspan of 65 meters and AR of 7.7. (a)Assuming take off weight of 910,000 pounds and a take off velocity 160 knots, calculate the lift coefficient at take off for standard sea-level conditions.(b) Compare the above result with the lift coefficient for cruise at Mach number of 92% of the speed of sound.
A straight-tapered flying-wing aircraft has the following characteristics: span, 20 ft; area, 100 ft2 ; root chord, 6 ft; tip chord, 4 ft; leading-edge sweep angle, 40 deg; sweep angle of line of maximum thickness, 24 deg; and Airfoil NACA 2412. Determine the wing's lift-curve slope and induced drag k value. Assume the flight Mach number is 0.25 in standard sea-level conditions.
Consider the same Lockheed F-104 supersonic fighter shown, with the same flight conditions of Mach 2 at an altitude of 11 km. For these conditions the wing angle of attack is α = 0.035 rad = 1.98◦. Assume the chord length of the airfoil is 2.2 m, which is approximately the mean chord length for the wing. Also, assume fully turbulent flow over the airfoil. Calculate: (a) the airfoil skin friction drag coefficient, and (b) the airfoil wave-drag coefficient. Compare the two values of drag.
1. Describe the flow phenomenon and mechanism of suddencontraction and sudden expansion shown in demonstration board.2. What are the advantages and the disadvantages of the multi-elementairfoil?3. Make a comparison of the airflow between an infinite wing and afinite wing.4. Sketch the forces on a Ping Pang ball when it is stable in an air jet.
Good day. Here is my question (10) Consider a low-speed subsonic wind tunnel with a 12/1 contraction area ratio for the nozzle. If the flow in the test section is at a standard sea level conditions with a velocity of 50 m /s, calculate the height difference in a U-tube mercury manometer with one side connected to the nozzle inlet and the other to the test section. ρHg = 13.6 x 103 kg/ m^3.
A B-2A is flying at 42,500 ft in standard day conditions at 420 KTAS. The mean chord length is 39.6ft.B) Find the percentage of the wing chord where laminar flow is present if the Reynolds number is500,000.
The particle in Fig is moving in sea-level standardair. From the two disturbance spheres shown,estimate (a) the position of the particle at this instantand (b) the temperature in °C at the front stagnationpoint of the particle.

SEE MORE QUESTIONS

Recommended textbooks for you

Principles of Heat Transfer (Activate Learning wi…

Mechanical Engineering

ISBN:

9781305387102

Author:

Kreith, Frank; Manglik, Raj M.

Publisher:

Cengage Learning