Pu Wings at supersonic flows can be modeled as a flat plate that have constant pressure distributions across their chord. Ignoring any viscous effects determine the drag force of the wing section. Round to the full N/m and make sure you use the standard sign convention (i.e. right hand rule). Use the following data chord = 1.5 m epsilon = 5 degree angle of attack = 20.0 alpha upper surface pressure = 60,000 Pa lower surface pressure = 150,000 Pa %3D

Pu Wings at supersonic flows can be modeled as a flat plate that have constant pressure distributions across their chord. Ignoring any viscous effects determine the drag force of the wing section. Round to the full N/m and make sure you use the standard sign convention (i.e. right hand rule). Use the following data chord = 1.5 m epsilon = 5 degree angle of attack = 20.0 alpha upper surface pressure = 60,000 Pa lower surface pressure = 150,000 Pa %3D

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 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

See similar textbooks

Similar questions

Consider two pressure taps along the wall of a laminar boundary layer as in Fig. The fluid is air at 25°C, U1 = 13.7 m/s, and the static pressure P1 is 2.96 Pa greater than static pressure P2, as measured by a very sensitive differential pressure transducer. Is outer flow velocity U2 greater than, equal to, or less than outer flow velocity U1? Explain. Estimate U2
The Blasius boundary layer profile is an exact solution of the boundary layer equations for flow over a flat plate. However, the results are somewhat cumbersome to use, since the data appear in tabular form (the solution is numerical). Thus, a simple sine wave approximation. is often used in place of the Blasius solution, namely, u(y) ≅ U sin (?/2 y/?) for y < ?, and u = U for y ≪ ?, where ? is the boundary layer thickness. Plot the Blasius profile and the sine wave approximation on the same plot, in nondimensional form (u/U versus y/?), and compare. Is the sine wave profile a reasonable approximation?
Air equivalent to one of a standard height of 4000 m flows at 450 mi/h over a wing with a thickness of 18 cm, a chord of 1.5 m, and a wingspan of 12 m. What is the appropriate value of the Reynolds number to correlate lift and drag on this wing?
Consider a rectangular wing mounted in a wind tunnel. The wing model completely spans the testsection so that the flow sees essentially an infinite wing. The wing has a NACA 2421 airfoil section,a chord of 3.0 m, and a span of 20 m. The tunnel is operated at the following test conditions: P =101,000 N/m2; T = 35° C; V = 50 m/s; and µ = 1.9 * 10 -5 kg/(m s).(a) Determine the operating Reynolds number.(b) Calculate the lift, drag, and moment about the aerodynamic center for an angle of attack of 8 deg andRe=9*106(c) At a Reynolds number of 3 * 106, find the following:1) What is the stalling angle of attack for this airfoil?2) What is the angle of attack for zero lift?3) What is the lift-curve slope?
Assume that the Flettner rotor ship of Fig. has a waterresistance coefficient of 0.005. How fast will the shipsail in seawater at 20°C in a 20-ft/s wind if the keel alignsitself with the resultant force on the rotors? [Hint: This is aproblem in relative velocities.]
A C-130 pilot desires to fly a low-level navigation mission at 4 n miles/ min (240 kn ground speed).Winds are forecast out of the north (blowing south) at 20 kn, the pressure altitude is 10,000 ft, andthe temperature is 80 °F. What indicated airspeed should the pilot fly on a northbound leg if theposition error is negligible? The answer is q = 136 lb/ft2
Air at 20°C and 1 atm flows at 2 m/s past a sharp flat plate.Assuming that Kármán’s parabolic-profile analysis, , is an accurate, estimate (a) the local velocity u and (b)the local shear stress τ at the position (x, y) = (50 cm, 5 mm).
Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2(2116 lb/ft2), respectively. Consider the flow field over a circular cylinder mounted perpendicular tothe flow in the test section of a low-speed subsonic wind tunnel. Atstandard sea level conditions, if the flow velocity at some region of theflow field exceeds about 250 mi/h, compressibility begins to have an effectin that region. Calculate the velocity of the flow in the test section of thewind tunnel above which compressibility effects begin to become important, i.e., above which we cannot accurately assume totallyincompressible flow over the cylinder for the wind tunnel tests.
Some engineers want a good estimate of drag and boundary-layerthickness at the trailing edge of a miniature wing. The chord and span ofthe wing are 6 mm and 30 mm, respectively and a typical flight speed is5 m/s in air (kinematic viscosity = 15 × 10−6 m2/s; density = 1.2kg/m3). An engineer may decide to make a superseding model withchord and span of 150 mm and 750 mm, respectively. Measurements onthe model in a water channel flowing at 0.5 m/s (kinematic viscosity = 1× 10−6 m2/s, density = 1000 kg/m3) give a drag of 0.19 N and aboundary-layer thickness of 3 mm. Estimate the corresponding values forthe prototype
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. kindly give me the solution of this problem with correct and logical reasoning.
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. I got the first solution which was wrong kindly solve it correctly
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s