Problem 2: Consider the Boeing 747 jet transport, whose layout is shown in Fig. 2 and has thefollowing characteristics:xoa 0.25, 8 5500/2, b 195.68ft, 27.31ft, AR, 3.57, V = 0.887Determine the wing and tail contributions to the CM-a curve.You may want to assume CM,reasonable assumptions (e.g.,-0.09, 0, -4°. i=0.0°, and i = -2.0°. Make any other0.9).

Answered: Image /qna-images/answer/da6da5e4-4d1d-485f-89b8-769199d9c9da.jpg

Answered: Problem 2: Consider the Boeing 747 jet…

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 following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image. Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed Aircraft lift-off speed 155 knots Max take-off gross weight 220 tonnes Wing planform area (S) 358 m Wing CL (t/o flaps deployed, a = 0) 1.1 Wing span 53.18 m Oswald efficiency factor, e 0.7 KGE = CD(IGE) / Co(OGE) 0.4 Co sum (fuselage, wing, tailplane and nacelle) 0.015 Co for undercarriage 0.021 Co for flaps at taking-off setting 0.0073 Coefficient of rolling friction, u 0.02 Engine thrust (assumed constant) 310 kN per engine It may be assumed that 1knot = 0.51444 m/s It may be assumed that 1knot = 0.51444 m/s
3. Suppose the drag force on a truck is given by the equation: F = cqu² + c2v where c = 4.80 N and c, = 111.8 N. Check that this relationship is plausible. Do the units work out? (a) Calculate the required propulsive power at a speed of 55 mi/hr. Express your final answer in Hp. Recall that 1Hp= 745.7 W. (b) Calculate the required propulsive power at a speed of 80 mi/hr. (c) Is the ratio of required powers proportional to the ratio of given speeds? Surprised? Or not?
An aircraft has the CL-a curve shown in Figure 4.12. The following data applies: Weight = 20 000 lb Wing area, S = 340 sq. ft. Density altitude = 10 000 ft TAS 242.4 kts. Find the aircraft's AOA for steady. CL 1.6- 1.4- 1.2- 1.0 0.8 0.6 0.4 0.2 0 L 02 ----Straight portion Clux J 1 4 6 8 10 12 14 16 18 Angle of attack (a) Eigure 4.12 C vs. AOA for a symmetrical airfoil. Stall angle of attack
Need help with this engineering problem.
Consider a thin aerofoil, with mean camber line in the form of a circular arc, with mean camber given by the image provided. f is the maximum camber Find the lift coefficient, the zero lift AOA, the moment coefficient about the leading edge, the moment coefficient about the aerodynamic centre and the location of theaerodynamic centre
A velomobile is a bicycle or tricycle with a full aerodynamic fairing. The aerodynamics of a velomobile are far better than a cyclist on a typical mountain bike. We are going to assume the rider has a mass of 70 kg.
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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 °C (Note: Take Air Density at 30 °C) Required: - Find Lift and Drag Coefficient at 15 Degree Attack Angle.
5.2 Consider the following aircraft flying in straight and level unaccelerated trimmed flight at M 0.2 at sea level. MAC 12 ft Xeg W Xcg 0.5cwing Macail Macit = -5000 ft lb = 0 ac wing T = 3000 lb W = 12,000 lb Ctail =4 ft bwing = 30 ft Cwing = 8 ft (a) Find the lift of the wing and the lift of the tail. Assume Lwing and Ltail act at the quarter chord points. (b) Find the aircraft drag. (c) Assuming a rectangular wing, what is the total aircraft C,? (d) What is the pitching moment coefficient for the entire aircraft?
A 1:7 scale model simulates the operation of a large turbine that is to generate200 kW with a flow rate of 1.5 m3/s. What flow rate should be used in the model, andwhat power output is expected?(a) Water at the same temperature is used in both model and prototype.(b) The model water is at 25°C and the prototype water is at 10°C.
The lift coefficient when the angle of attack (AOA) is given as 3°.
You are given a drone with an average chord length of 8 in., a wingspan of 2.5 ft, and a weight of 300 g. Based on figure 2, would it stay in the air at a speed of 5 m/s? (Assume ρ=1.225 kg/m3 and Nu=1.516*10-5 m^2/s)

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