Answer this ole b) For an aerofoil similar to NACA 2412, the lift coefficient and moment coefficient aboutthe quarter-chord at -8° AOA are found to be -0.6 and -0.0466, respectively. At 6° AOA,these coefficients are found to be 0.86 and -0.0354, respectively.Giving reasons for your method, calculate the zero lift AOA and the location of theaerodynamic centre.

Detailed explanation: Let's break down the problem step by step. Given Information:Airfoil type:…

Answered: b) For an aerofoil similar to NACA…

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

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The Drag Polar Equation of an General Aviation Aircraft in clean configuration can be written as: C2 Cp = 0.0270+ %3D 32.787 Its weight is 2300 lb and the wing area is 155ft?, Calculate the (L/D)max and the Minimum Thrust Required (Unaccelerated Level flight and Sea level Condition)
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.
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.
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 large transport aircraft shown below whose gross weight is 100,000 lb. The airplane pitching mass moment of inertia Iy=40,000,000 lb-s2 in. The airplane is making a level landing with the nose wheel slightly off the ground. The reaction on the rear wheels is 319,000 lbf inclined at such an angle to give a drag component of 100,000 lb and a vertical component of 300,000 lb. Determine: a) The intertial forces on the airplane. b)The resultant load on the pilot whose weight is 180 lbm and whose location is as given in the figure.
The original Flettner rotor ship was approximately 100 ftlong, displaced 800 tons, and had a wetted area of 3500 ft2. Assketched in Fig. , it had two rotors 50 ft high and 9 ft indiameter rotating at 750 r/min, which is far outside the range. The measured lift and drag coefficients for eachrotor were about 10 and 4, respectively. If the ship is mooredand subjected to a crosswind of 25 ft/s, as in Fig. whatwill the wind force parallel and normal to the ship centerlinebe? Estimate the power required to drive the rotors.
q: An aircraft is flying straight and level at a certain altitude with a velocity of 214 fps. Determine the power required if the wing area is 115 ft? and the total drag coefficient is 0.067. Assume SSLC (p=0.002377 slug/ft3). Provide answer in ft-Ib/s. and round off to the nearest whole number. Solve using standard English units.
A fl at-plate airfoil with C = 1.2 m is to have a lift of30 kN/m when fl ying at 5000-m standard altitude withU∞= 641 m/s. Using Ackeret theory, estimate (a) the angleof attack and (b) the drag force in N/m.
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2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Yu 0 0.0952 0.0922 0.0588 0 Fx = dYu dx 5 Y₁ 0 -0.0254 -0.0144 -0.0052 0 PL Pd) d: dx Y = Yu (x) Calculate the drag and lift force on the airfoil by numerically evaluating the integrals = S₁² ( P₂₁ = ['(P₁ - F (P₁ - Pu)dx 0 y = Y₂ (x) Pu 1.000 -1.640 -0.786 -0.212 0 Fy x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.
Determine the velocity required for take off for an aircraft with the following characteristics.Aircraft mass: 7200 kgWingspan: 15 mWing shape: rectangularWing chord length: 1.8 mWing airfoil: NACA 4415Wing angle of attack: 7× 0.5 + 5 degreesHint: Check NACA charts for required parameters.
a)What is the impact of increasing Reynolds number on skin friction and pressure drags over an airfoil? What can be happened for separation in this case? b) What is an adverse pressure gradient and where does it occur on an airfoil (show that on a sketch)? c) Why lift-to-drag ratio is an important parameter for an aircraft? d)How can changing in altitude affect the aircraft power required, PR? Show thatmathematically and graphically?

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