Answered: A turbojet engine weight 7 kN and has a…

A turbojet engine weight 7 kN and has a wing area of 20 m2. The drag coefficient of aircraft is given by CD =0.01+0.02 CL?, and the maximum lift coefficient is 1.2, determine Vstall :

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

See similar textbooks

Related questions

Q: Calculate lift, drag and (T/W ratio) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a…

A: Given data U∞=500 m/sA=45 m2CD=0.05CL=0.9

Q: Force acting on a truck (frontal area of 2.01 m?) in the flow direction as shown is measured…

A: A=2.01 m2F=x+100 N where x=190.6 soF=190.6+100 F=290.6 NP0=1 atm T0=20 °CU=95kmhU=95×518=26.388…

Q: Qustion. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2…

Q: An aircraft is equipped with a wing of symmetrical airfoils. The lift curve slope of the total…

A: Mach number: the ratio of the fluid velocity to the velocity of sound is known as the Mach number.…

Q: of drag coefficient Cd?

A: E. dimensionless

Q: Calculate the minimum flight speed of an aircraft at constant altitude. Consider and aircraft with…

Q: The measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1,and αL=0 = −1.3◦. Consider a…

A: Given Data: The taper ratio is: 0.8 The slop of the airfoil is: a0=0.1080 degree-1. The aspect…

Q: The power delivered to the wheels of a car is used to overcome aerodynamic drag. Compare the amount…

Q: A jet airplane weighs 160,000 N and has a zero-lift drag coefficient of 0.008 and a wing area of 42…

A: Write the given data for the airplane. W=160000 NCD0=0.008 A=42 m2 v=100 m/s rc=11.5…

Q: The velocity profile for boundary layer over a 73 1 y 3 Ux flat plate is given by, u. y 2 8x 2 8x…

A: The solution is given below

Q: Consider a NACA 2412 airfoil at an angle of attack of 4 degrees. If the freestream Mach number is…

Q: The resultant of the pressure and wall shear forces acting on a body is measured to be 470 N, making…

A: Given data as per question Force =470 N Angle = 330

Q: A streamlined experimental solar car has a frontal area of 0.48 m² and an expected coefficient of…

Q: What is the effect of increasing the airfoil angle of attack on lift and flight? Brie- explain with…

A: Up to a certain degree, increasing the angle of attack increases lift and produced drag. When…

Q: A new car is introduced and has a drag coefficient of 0.30 and a frontal area of 1.95 sqm and is…

Q: A light combat aircraft weighs 75,000 N and has a wing area of 27 m2. The maximum lift coefficient…

Q: When the "Area rule" is applied, which aerodynamic coefficient it affects the most? O drag…

A: According to area rule two panes with same longitudinal cross sectional area distribution have same…

Q: The two spheres stand with a stop element as in the figure. The spheres are connected with…

Q: What is the formula and variables in finding the air drag of a motorcycle?

A: Given question: What is the formula and variables in finding the air drag of a motorcycle. The given…

Q: , A small aircraft has a wing area of 40 m2a lift coefficient of 0.45 at takeoff settings, and a…

Q: The resultant of the pressure and wall shear forces acting on a body is measured to be 430 N, making…

A: Given: The resultant of the pressure and wall shear forces acting on a body is F=430 N. The angle…

Q: An airplane has a mass of 50,000 kg (without load), a wing area of 360 m2 , a maximum lift…

Q: Study how the lift and drag varies with a change in angle of attack for a flat plate, symmetrical…

A: Validation of the sectional airfoil performance is necessary to test a propeller. This study…

Q: A glider weighing a 600lbf has a wing loading of 15lbf/ft?. Its drag equation is: Cp 0.014 + 0.05c…

A: Given data Weight of glider = 600 lbfWing loading = 15 lbf/ft2Drag equation is CD = 0.014 + 0.05…

Q: 5) A wedge airfoil is placed in a supersonic flow at M 2. G. Calculate the lift and drag…

A: Given: The Mach number, M = 2.G = 2.2 The angle of attack, α = 4°

Q: In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required…

Q: What is the Effect of wing plan form (taper ratio and wing twist) and aspect ratio(AR) on the…

A: Wing plan form affects drga coefficient and lift. In this aspect ratio is given as ratio bet wind…

Q: A jet powered airplane, having the following characteristics in steady level flight: rectangular…

A: Wing arae. S=20 m2Normal gross mass, m=8986 kgLift coefficient, CL=1.33Parasite drag coefficient,…

Q: An airplane has a total mass of 35,000 kg and a wing planform area of 65 m2. The airplane is…

A: Given: the velocity of the plane, V=1100 km/h=1100×10003600=305.556 m/s Ballance the lift force with…

Q: ler angles of attack, which is associated wi Diffuser effect Дифузорно течение O a decrease in Lift…

A: Solution ;

Q: 1. Consider an light plane aircraft with a characteristic of: Wing area = 181 ft2 Aspect ratio =…

A: Solution: Given Data: A=181 ft2AR=6.2ηo=0.91W=3000 lbCD,o=0.027Pmax=345 hpηp=0.83V∞=100 ft/s Note:…

Q: At subsonic speeds, how do the lift coefficient CL and drag coefficientCD for a wing vary with angle…

A: When the angle of attack increases, the flow separation on the upper surface of the wing becomes…

Q: The drag coefficient of a vehicle increases when its windows are rolled down or its sunroof is…

A: Given data: The frontal area of the car, A = 18 ft2. Drag coefficient when the sunroof is closed,…

Q: lift coefficient CL=? with calculated magnitude of lift force from potential flow theory

A: Given that radius of 5 m length of 3 m air having a density ρ=1,2 kg/m3 free-sream speed of 3 m/s…

Q: b) Figure Q1(b) shows a smooth flat plate that is 150 mm wide and 500 mm long placed longitudinally…

A: Drag force: The drag force is the force acting opposite to the direction of fluid flow. Due to its…

Q: Determine the lift coefficient of a supersonic aerofoil, approximated by a flat plate. It is flying…

A: Introduction: The lift coefficient (CL), a dimensionless coefficient, connects the lift produced by…

Q: P6.31 (a) A luxury sports car has a frontal area of 2.08 m? and a 0.29 coefficient of drag at 95…

A: Given data: (a) The frontal area of the car is A=2.08 m2 The coefficient of drag is CD=0.29 The…

Q: A person is driving his motorcycle at a speed of 90 km/h in air at 20°C. The frontal area of the…

A: Given: The speed of motorcycle is V=90 km/h. The temperature of air is T=20°C. The frontal area of…

Q: - Study how the lift and drag varies with a change in angle of attack for a flat plate, symmetrical…

A: The impact is called induced drag or drag due to lift. The flow around the wingtips of a finite…

Q: Calculate lift, drag and (T/W) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag…

A: Given, V = 500 m/s A = 45 m2 CD = 0.05 CL = 0.9

Q: The resultant of the pressure and wall shear forces acting on a body is measured to be 430 N, making…

A: The drag force FD=FRcos30°=430cos30°=372.4N

Q: A new sports car has a drag corfficient of 0.30 and a frontal area of 18.5 ft2, and is traveling at…

Q: An airplane has a total mass of 18,000 kg and a wing planform area of 40 m2. The density of air at…

A: Solution: Weight of the airplane=18000×9.81=176580N Wing Area=40m2 Density of air=1.2kg/m3 Max lift…

Q: An airplane is consuming fuel at a rate of 7 gal/ min when cruising at a constant altitude of 10,000…

A: Take the following assumptions. Standard atmospheric conditions exist. The settings of the plane…

Q: n aircraft has the drag polar, C_d=0.015+0.05C_l^2 For a lift coefficient of 0.5, find the value of…

A: Given:Drag polar, Cd=0.015+0.05Cl2Lift coefficient, Cl=0.5

Q: Air is flowing past a spherical ball. Is the lift exerted on the ball zero or nonzero? Answer the…

A: When air is flowing past a spherical ball, the lift exerted on the ball is zero if the ball is…

Q: determined experimentally. If the frontal area of the car is 2 m?, and the force acting on the car…

Concept explainers

Numerical Calculations

In the mid-20th century, the availability and the growth in power of digital computers led to the increase in the mathematical model in the field of engineering and science. The analysis of these detailed models needs to be increased.

Question

chose the correct answers

4. *
A turbojet engine weight 7 kN and has a wing area of 20 m². The drag coefficient
of aircraft is given by CD 0.01+0.02 CL?, and the maximum lift coefficient is 1.2,
determine Vstall :
20 - 25 m/s
15 - 20 m/s
30 - 35 m/s
25 - 30 m/s

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

SEE SOLUTION Check out a sample Q&A here

Given

VIEW

Step 1

VIEW

Step by step

Solved in 2 steps

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

An aircraft has the drag polar, C_d=0.015+0.05C_l^2 For a lift coefficient of 0.5, find the value of the drag coefficient and lift drag ratio?
What is the effect of Reynolds number on drag coefficient , lift coefficient and L/D ratio
What is the formula and variables in finding the air drag of a motorcycle?
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 .
The Antonov An-225 is the heaviest aircraft ever built, with a maximum takeoff weight of 640 metric tonnes. It also has the largest wingspan of any aircraft in operational service. Sea level standard day (sls) conditions for calculations are 15°C; 101.3kPa Rotate speed (Vr) at takeoff (sls): Vr = 154 kts = 1.2×Vmin (1 kt = 0.514 m/s) Cruise Engine Thrust : a) Calculate the lift coefficient for a standard day takeoff b) Calculate the drag coefficient at cruis Fcruise = 0.85 Fmax Engine maximum thrust: Factual,max = Fsls,max×δ θ½ δ = Pactual/Pref; and θ = Tref/Tactual
A new sports car has a drag corfficient of 0.30 and a frontal area of 21ft^2, and is traveling at 110 mi/h. How much power (in ft-lb/s) is required to overcome aerodynamic drag if air density is 0.002378 slugs/ft^2?
A new sports car has a drag corfficient of 0.30 and a frontal area of 18.5 ft<, and is traveling at 90 mi/h. How much power (in ft-lb/s) is required to overcome aerodynamic drag if air density is 0.002378 slugs/ft?
A 17,000-kg tractor-trailer rig has a frontal area of 9.2 m2, a drag coefficient of 0.96, a rolling resistance coefficient of 0.05 (multiplying the weight of a vehicle by the rolling resistance coefficient gives the rolling resistance), a bearing friction resistance of 350 N, and a maximum speed of 110 km/h on a level road during steady cruising in calm weather with an air density of 1.25 kg/m3. Now a fairing is installed to the front of the rig to suppress separation and to streamline the flow to the top surface, and the drag coefficient is reduced to 0.76. Determine the maximum speed of the rig with the fairing.
What is necessary to increase the Lift to Drag ratio and its Maximum value?
A new car is introduced and has a drag coefficient of 0.30 and a frontal area of 1.95 sqm and is traveling at 195 km/h. How much power is required to overcome aerodynamic resistance if air density is 1.325 kg/m^3?
For a 10 deg included angle wedge at 0 deg AOA, calculate the lift and drag coefficient (Cl = 0, Cd = 0.082). Then calculate the lift and drag at AOA=4 deg (Cl = 0.16, Cd = 0.093). Let M=2.
19) You're flying a plane with a max speed of 267 ft/s and a wing area of 175ft^2 and a lift coefficient of 0.205, your plane weighs 2000lbs. What is the smallest radius turn you can make at 5000ft of altitude(where the air is 0.002048 slug/ft^3) at a constant speed without loosing altitude?