CAN SomeOne solve part c 6.3Consider an airplane patterned after the Fairchild Republic A-10, atwin-jet attack aircraft. The airplane has the following characteristics:wing area = 47 m², aspect ratio = 6.5, Oswald efficiency factor = 0.87,weight = 103,047 N, and zero-lift drag coefficient = 0.032. The airplaneis equipped with two jet engines with 40,298 N of static thrust each atsea level.a.Calculate and plot the power-required curve at sea level.b. Calculate the maximum velocity at sea level.C.d.Calculate and plot the power-required curve at 5-km altitude.Calculate the maximum velocity at 5-km altitude. (Assume theengine thrust varies directly with free-stream density.)

Answered: Image /qna-images/answer/3abb20b5-9034-460b-bb1b-fd51649468eb.jpg

Answered: 6.3 Consider an airplane patterned…

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

1
An axial flow water pump impeller consists of 5 blades with chord length 3 in., hub radius 4.5 in. and tip radius 6.5 in. The impeller isrotating at 1800 rpm and the lift and drag coefficients are given as 1.32 and 0.027 respectively. If the inlet and exit blade angles are 50° and 25° respectively, and the stagger angle is 30°, determine: a) Angle of attack b) Lift and drag forces (Ibf) c) Exit flow angle
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.
The Drag Polar Equation of an General Aviation Aircraft in clean configuration can be written as: C2 Cp = 0.0270+ %3D 32.787 Its weight is 2300 lb and the wing area is 155ft?, Calculate the (L/D)max and the Minimum Thrust Required (Unaccelerated Level flight and Sea level Condition)
An airfoil has a lift curve slope at 7/rad and angle at zero lift of -3deg. At what angle of attack will the airfoil develop a lift of 120 lbs/ft at 110 mph under SSLC? Assume c = 10ft.
Q.17. A Kite Weighing 9.8 N and having an area 1 m makes an angle of 7° to horizontal when flying in a wind of 386 km/h. If pull on the string attached to the kite is 49 N and it is inclined to the horizontal at 45°. Calculate the lift and drag coefficients. Take p for air = 1.2 kg/
Determine the velocity required for take off for an aircraft with the following characteristics.Aircraft mass: 7200 kgWingspan: 15 mWing shape: rectangularWing chord length: 1.8 mWing airfoil: NACA 4415Wing angle of attack: 7× 0.5 + 5 degreesHint: Check NACA charts for required parameters.
What’s the answer for this please ?
7. A 2700-lb car is traveling @ 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 ft, what is its drag coefficient?
If the pressure difference in the wind tunnel experiment is 50 mmH,0, the density of air is 1.2 kg/m in wind tunnel experiment, and the airfoil span is 204 mm, and the cord length is 98 mm, what is the lift coefficient if the lift force is L=13.4 N
A conventional low speed aircraft had the following aerodynamic characteristics: CDo=0.020. e=1.0 (Oswald efficiency). The aircraft was flown to maintain a steady level flight and for minimum thrust required, at a lift coefficient of Cz=0.8. The numerical value of the aspect ratio of the wing is three decimal places). (in
4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil Eg. (4,57) C 2.0 - 1.e 1.2 Lift coefficient 0.8 0.4 -0.4 Eg. (4,64) -0.1 Moment coefficient -0.8 -0.2 -1.2 -0.3 Re - 3.1 X 10 O Re- 8.9 x 10 -0.4 16 a, degrees de; = ? da

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