3. A conventional aircraft (tail to the rear), is in trimmed, level, unaccelerated flight. Thewing is generating 40,000 lbs of lift and has a moment around the aerodynamic center of -20,000 ft-lb. The aerodynamic center of the wing is located at 0.25c, the center of gravityis located at 0.45c, the aircraft has a chord of 5 ft, and the symmetric tail aerodynamiccenter is located 10 ft behind the center of gravity. What is the lift generated by the tail andwhat is the weight of the aircraft? {Hint: Draw a sketch and assume thrust and all dragforces act through the center of gravity.

Answered: 3. A conventional aircraft (tail to the…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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An airfoil has a chord equal to 2 m. The center of pressure is located at the 40% of the chord from the leading edge. The resultant aerodynamic force R = 10 N, and acts in the direction such that angle \theta = 85 deg. Calculate the aerodynamic moment around the quarter-chord point (Mc/4), the leading edge (MLE), and the trailing edge (MTE)? (When calculating moments, indicate the sign “+” or “-”.)
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 wing of an aircraft haa a taper ratio of 0.63, and mean aerodynamic chord of 2.65ft. find the measurement of the wing's root chord, tip chord and wing area if the wingspan is 30 ft
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Aerodynamic Model: - Circular Disk Inside Dia.= 40 mm Outside Dia.= 80 mm Angle of Attack= 15 Degree Lift Force= 0.38 N Drag Force=0.40 N Wind Velocity= 20 m/sec Air Temperature= 30 oC (Note: Take Air Density at 30 oC) Required: - Find Lift and Drag Coefficient at 15 Degree Attack Angle.
4
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A smooth square billboard 5 × 5 m² is place on a roof of a tall building. In orienting the billboard, the engineer is considering the wind direction for two possible cases: (a) the wind is parallel to the board (b) the wind is perpendicular to the board. Assuming maximum wind velocity of 10 m/s, what will be the force acting on the billboard in each of the cases considered? (Use u = 1.85 x 10-5 kg/m – s; p= 1.225 kg/m³; Recr = 500,000) %3D
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4. The Wright brothers used a very thin wing on their 1903 flyer. In addition, they made extensive use of a homebuilt wind tunnel to test their wing designs. span, b chord, c Model of Wright Flyer (a) The Wright's wind-tunnel models had chord length, c, of about 0.04 m and wing span (length) of 0.26 m. The wind tunnel operated at approximately the same wind speed as the full-scale aircraft - about 13 m/s. Estimate the drag (friction) of a single wind-tunnel model wing under standard conditions (p = 1.225 kg/m³, μ = 1.7894 × 10-5 kg/s-m). Note that the wing is mounted in the wind tunnel so that both upper and lower surfaces are exposed to the flow. (b) The full-scale 1903 flyer had a chord length of 1.9 m and a wing span of 12.3 m. Estimate the drag (friction) of a single full-scale Wright flyer wing flying at 13 m/s under standard atmospheric conditions. (c) Consider the main wing configuration, which consisted of two wing surfaces (biplane) connected by 181 cylindrical rods. We will…
please answer do not image format
5) Explain the causes of Lift and Drag on the illustration below: Airfoil Lift motion Drag a.

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