Effect velocity on drag force 1.lf you were this choosing this aerofoil for use on an aircraft what incidence angle would give the best performance and why ? 2.From your result, how can tell that the aerofoils have a symmetricał section 3.How AoA effect on the (CD)? 4.Comment on how the foces and coefficients of drag vary with incidence angle 5.What the relationship stall ,drag ?

Effect velocity on drag force 1.lf you were this choosing this aerofoil for use on an aircraft what incidence angle would give the best performance and why ? 2.From your result, how can tell that the aerofoils have a symmetricał section 3.How AoA effect on the (CD)? 4.Comment on how the foces and coefficients of drag vary with incidence angle 5.What the relationship stall ,drag ?

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...

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You are designing an airfoil for a new hobby RC plane. Because of your limited knowledge, you have mistakenly approximated your airfoil as an ellipse with a = 75mm and b = 12mm. Here, “a” is the depth of your wing and “b” is the thickness. Your plane travels through the air at approximately 20mph (8.9m/s). As it does so, skin friction produces a drag-induced heat of 800W on your wind, of length 1m. Properties of Air: k = 0.025 W/mK, Pr = 0.72, v = 1.847 x 10−5, u = 16.84 x 10−6, p = 1.2 kg/m3, B = 1/Tf (ideal gas), TInfinity = 25oC a) What is the Reynold’s number? Hint: “D” is taken to be the thickness for an elliptical crosssection. b) What is the Nusselt number? c) What is the convection coefficient? d) What is the average temperature of your wing? Assume an ellipse perimeter of approximately 200mm.
The large block shown is x = 72 cm wide, y = 54 cm long, and z = 9.0 cm high. This block is passing through air (density of air p = 1.43 kg/m³) at a speed of v = 8.61 m/s. Find the drag force F41 acting on the block when it has the velocity vj and a drag coefficient I = 0.812. V2 Fa.1 N %3D Find the drag force F42 acting on the block when it has the velocity vz with a drag coefficient I = 0.893. F42 N Find the drag force Fa.3 acting on the block when it has the velocity vz with a drag coefficient I = 1.06. F4.3 = N EN
You are designing an airfoil for a new hobby RC plane. Because of your limited knowledge, you have mistakenly approximated your airfoil as an ellipse with a = 75mm and b = 12mm. Here, “a” is the depth of your wing and “b” is the thickness. Your plane travels through the air at approximately 20mph (8.9m/s). As it does so, skin friction produces a drag-induced heat of 800W on your wind, of length 1m. Properties of Air: k = 0.025 W/mK, Pr = 0.72, v = 1.847 x 10−5, u = 16.84 x 10−6, p = 1.2 kg/m3, B = 1/Tf (ideal gas), TInfinity = 25oC a) What is the average temperature of your wing? Assume an ellipse perimeter of approximately 200mm.
If a missile takes off vertically from sea level and leavesthe atmosphere, it has zero drag when it starts and zerodrag when it finishes. It follows that the drag must be amaximum somewhere in between. To simplify the analysis,assume a constant drag coefficient, CD, and constant verticalacceleration, a. Let the density variation be modeled by thetroposphere relation. Find an expression for thealtitude z* where the drag is a maximum. Comment onyour result.
Aerodynamics NACA 664-221 Chord c = 150 cm 1) What is the CL range to achieve the minimum coefficient of drag? 2) What is the thickness ratio of the airfoil?
Q4) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force and coefficiet of drag in terms of Re for the velocity profile of laminar boundary layer u/U=4(y/8)-6(y/8)5. Calcate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 1m long and 0.5m wide at a velocity 0.9m/s, the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
Define flow separations both statement and formulations around and along an airfoil in flow direction. Depending on the angle of attack, how can you retard/delay/diminish/control/postpone/decrease the flow seperation on airfoil? Write down at least five methots, briefly describe and draw schematic figures for each method.
simple answer a)What is an adverse pressure gradient, and where does it occur on an airfoil (Show that onan airfoil using a free hand sketch)? b) Why do golf balls have dimples? Hint: Support your answer by a sketch
Icebergs can be driven at substantial speeds by the wind.Let the iceberg be idealized as a large, flat cylinder, D >> L,with one-eighth of its bulk exposed, as in Fig.. Letthe seawater be at rest. If the upper and lower drag forcesdepend on relative velocities between the iceberg and thefluid, derive an approximate expression for the steady icebergspeed V when driven by wind velocity U.
A NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level conditions. The freestream velocity is 70 m/s. Given the lift per unit span is 1,254 N/m. By using the experimental data for NACA 2412 data plot in Figure Q1c, investigatethe angle of attack of the airfoil and the analyze the value of drag per unit spanof the airfoil. Given that at standard sea level, ?=1.789×10-5 kg/m.s.
The so-called Rocket Man, Yves Rossy, fl ew across the Alps in2008, wearing a rocket-propelled wing-suit with the followingdata: thrust = 200 lbf, altitude = 8,200 ft, and wingspan = 8 ft(http://en.wikipedia.org/wiki/Yves_Rossy). Further assume awing area of 12 ft2, total weight of 280 lbf, CDq = 0.08 for thewing, and a drag area of 1.7 ft2 for Rocket Man. Estimate themaximum velocity possible for this condition, in mi/h.
When immersed in a uniform stream V, a heavy rod hingedat A will hang at Pode’s angle θ, after an analysis by L.Pode in 1951 (Fig.). Assume that the cylinder hasnormal drag coefficient CDN and tangential coefficient CDTthat relate the drag forces to VN and VT, respectively. Derivean expression for Pode’s angle as a function of the flow androd parameters. Find θ for a steel rod, L = 40 cm, D = 1 cm,hanging in sea-level air at V =35 m/s.