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.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

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.
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
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
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.
The lift on a spinning circular cylinder in a freestream with a velocity of 22 m/s and at standard sea level conditions is 6 N/m of span. Calculate the circulation around the cylinder.
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
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 (o = 1.225 kg/m³, = 1.7894 x 10-³ 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…
5) Explain the causes of Lift and Drag on the illustration below: Airfoil Lift motion Drag a.
Problem 3 - A small airplane that has a mass of 1,500 lb,m is about to take off. The airplane has a coefficient of lift of 1.0 at an Angle of Attack (AOA) of zero and it linearly increases by 0.1 every 10 degrees; wings with a constant chord length of 3.5 ft and a total wingspan of 30 ft; a coefficient of drag of 0.3; and a frontal area of 40 ft? that linearly increases by 5 ft every 10 degrees. If the air is still, and the density of air is 0.076 lbm ft-3 at the ground level what is the critical speed needed for takeoff? If the runway is 1000 ft long, the total coefficient of friction between the road and the airplane is 0.25, what is the average thrust needed to achieve the critical takeoff speed?
Please do this specific question with these specific data as many have post it with different data! The ABC lift is at rest. You want to estimate the momentum that ABC exerts in C if the weight of A is 105 kg. AB is 12.15 m and weighs 400 kg, BC is 2.7 m and weighs 150 kg. Approximate AB and BC as evenly thick everywhere and homogeneous. Point A is 13.5 m above C in height and B is 2,025 m above C in height. A) What is the moment of force that ABC exerts in C if positive value is counterclockwise in the image? B) If AB instead weighs 150 kg and BC weighs 400 kg, but all other quantities are the same, calculate the torque in C.What is the moment of force that ABC exerts in C with these masses, if positive value is counterclockwise in the picture?
2.4 A 2650-lb car is traveling at sea level at a constant speed. Its engine is running at 4500 rev/min and is producing 175 ft-lb of torque. It has a drivetrain efficiency of 90%, a drive axle slippage of 2%, 15- inch-radius wheels, and an overall gear reduction ratio of 3 to 1. If the car's frontal area is 21.5 ft², what is its drag coefficient?
An aerospace engineer is designing a hover board for a project demonstration. He/She plans to use a single 3-ft-diameter blade span area for generating lift. The estimated overall weight of hover board system is less than or equal to 5 lbf. (a) How much exit velocity of air is to be achieved to lift the board (b) Volumetric flow rate needed

SEE MORE QUESTIONS

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS