Ign, McGraw-Hill,this chapter) and byNew York, 1999, for more information.EXAMPLE 6.18Estimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal= 0. The spoilers increase the zero-lift,used; however, spoilers are employed such that Ldrag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the wejehrof any fuel carried by the airplane. The maximum lift coefficient, with flaps fully employed at touchdown, is 2.5.

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of any fuel carried by the airplane. The maximum lift coefficient, with flaps fully em ployed at touchdown, is 2.5.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Fluid Dynamics

The study of the flow of gases and liquids, usually in and around solid surfaces, is known as fluid dynamics in physics and engineering. Fluid dynamics, for example, can be used to evaluate the movement of air through an airplane wing or the surface of a vehicle. It can also be used in ship design to increase the speed at which ships pass through water.

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Ign, McGraw-Hill,
this chapter) and by
New York, 1999, for more information.
EXAMPLE 6.18
Estimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal
= 0. The spoilers increase the zero-lift,
used; however, spoilers are employed such that L
drag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the wejehr
of any fuel carried by the airplane. The maximum lift coefficient, with flaps fully em
ployed at touchdown, is 2.5.

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! Required information Problem 06.001 - Calculate thrust required - DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL THE PARTS Consider an airplane modeled after the twin-engine Beechcraft Queen Air executive transport. The airplane has the following characteristics: weight is 38,220 N; wing area is 27.3 m²; aspect ratio is 7.5; Oswald efficiency factor is 0.9; and zero-lift drag coefficient CD,0 is 0.03. NOT Th is a multi-part question. Once an answer is submitted, you will be unable to return to this part. Problem 06.001.a - Calculate thrust required Calculate the thrust required to fly at a velocity of 525 km/h at standard sea level. Assume the value of poo = 1.225 kg/m³ at standard sea level. The thrust required to fly at a velocity of 525 km/h at standard sea level is N.
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An X-15 flew at a top speed of 4520 mph with a max altitude of 354,200 ft. a) What would the stagnation temperature on the nose of the airplane be under those conditions? b) calculate the % change in the values of cP, cV, and the specific heat ratio (k or g) from atmospheric to stagnation conditions.
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Question 2: Consider the 5000kg aircraft below being in a 1000m radius looping maneuver (Fig.2). There are 4 forces acting on the aircraft (Weight, Thrust, Lift, Drag). Assuming that they are all approximately perpendicular to eachother at points A,B,C, calculate the following: A. Calculate the Lift Forces at points A, B, C if the aircraft was at a constant speed of 350km/h throughout the maneuver. B. Calculate the Lift Forces at points A, B, C if the aircraft starts the maneuver at point A at a speed of 400km/h, but reduces its speed with constant acceleration so that the pilot feels weightless at point C. C. A human can withstand earth's gravity was more than 9 times what it is now, we would not survive. What is the maximum of 9 times the gravitational acceleration, i.e. if the maximum speed the pilot can enter this maneuver? Figure 2: Looping Aircraft
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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.