and power for part b 2. An airplane has a mass of 50,000 kg, a wing area of 300m², a maximum lift coefficient of 3.2, andcruising drag coefficient of 0.03 at an altitude of 12,000m. Determine (a) the takeoff speed at sea level;assuming it is 20 percent more than the stall speed, and (b) the thrust that the engines must deliver fora cruising speed of 700km/h. Andpart B.((@on)= 1.285P (@1000) = 0.312 kg/m³a./ take-off = 1.2x Ustall0powerfor(Ustall isU at which=wight • Lift fire)by Fr=

Answered: 2. An airplane has a mass of 50,000 kg,…

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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2. If the lift and drag coefficients in an airfoil are 0.998 and 0.05, respectively, determine by how many times the lift force is larger than the drag force in a blade with that airfoil profile.
A 0.25 kg kite with an area of 0.65 mitres squared flies in a 25 km/h wind such that the weightless string makes an angle of 40° relative to the horizontal.The density of air is 1.22 kg/m^3.if the pull on string is 7 N.determine the lift and drag coefficient basee on the kite area
An aircraft with symmetric airfoil of wing area 20 m2, flyingwith velocity 60km/hr experiences lift coefficient of 0.8. Considering the aircraft flying at sea level conditions, determine the mass of the aircraft.
Calculate the frontal area of a parachute of hemi-spherical shape which will allow aparachutejumper of weight 90 kg to descend with a steady velocity of 8 m/s ignoring air movement.The drag coefficient of parachute as determined from experiments is 1.5. Take the densityof air as 1.2 kg/m3
The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively.
A light combat aircraft weighs 75,000 N and has a wing area of 27 m?. The maximum lift coefficient with high-lift devices is 1.8, and the structural limit load factor is 6.0. While flying at 250 km/h, the aircraft makes a 90 deg turn in 8 s at sea level holding a constant altitude and at an angle of attack such that the lift-to-drag ratio is 8.0. Find (a) the bank angle, (b) load factor, (c) radius of turn, and (d) the thrust required. [Answer: (a) µ = 54.26 deg, (b) n = 1.7120, (c) R %3D 353.7665 m, and (d) T = 16,050 N.)
A jet airplane weighs 160,000 N and has a zero-lift drag coefficient of 0.008 and a wing area of 42 m2. At 100 m/s at sea level, the rate of climb is 11.5 m/s. The thrust developed by the engines is equal to 27,000 N. Determine the maximum rate of climb and the corresponding flight speed at sea level . [Answer: 21.6013 m/s and 214.5577 m/s]
What is the f (equivalent drag area) for an aircraft that creates 600 lbs of parasite drag at 10,000 ft STP and 250 KTAS?
A jet airplane weighs 160,000 N and has a zero-lift drag coefficient of 0.008 and a wing area of 42 m^2. At 100 m/s at sea level, the rate of climb is 11.5 m/s. The thrust developed by the engines is equal to 27,000 N. Determine the maximum rate of climb and the corresponding flight speed at sea level .
An airplane has a total mass of 18,000 kg and a wing planform area of 40 m2. The density of air at the ground is 1.2 kg/m3. The maximum lift coefficient is 3.48. The minimum safe speed for takeoff and landing while extending the flaps is (a) 199 km/h (b) 211 km/h (c) 225 km/h (d ) 240 km/h (e) 257 km/h
Q1 A car is traveling at sea level at a constant speed. It weighs 2500-lbs, has a frontal area of 20 ft² and has a 90% drivetrain efficiency. Its engine runs at 4000 rev/min, producing 168 ft-lb of torque. The drive axle slippage of 2%, 14-inch-radius wheels, and an overall gear reduction ratio of 2.5 to 1. What is its drag coefficient?
An airplane has a mass of 50,000 kg (without load), a wing area of 360 m2 , a maximum lift coefficient of 3.25, and a cruising drag coefficient of 0.03 at an altitude of 12,000 m. Taking the density of standard air as ρ1 = 1.225 kg/m3 at sea level and ρ2 = 0.312 kg/m3 at 12,000 m altitude. (a) Generate a plot of the safe takeoff speed at sea level Vs the load carried by airplane (ranging from 0 kg to 20,000 kg of load). (b) Determine the power that must be delivered by the engines for a cruising speed of 800 km/hr.

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