A flying wing weighing 20,000 N has a NACA 65‐418 airfoil section, an area of 30 m2, and an aspect ratio of 5.0. Determine the angle of attack for a sea‐level flight at 60 m/s. What is the lift‐to drag ratio? Assume that the nominal airfoil lift curve slope a0 = 0.106/deg̊, the profile drag CD0 = 0.0043 and e = 0.92. Problems1.1 A flying wing weighing 20,000 N has a NACA 653-418 airfoil section, areaof 30 m2, and an aspect ratio 5.0. Determine the angle of attack for a sea level flightat 60 m/s. What is the lift-to-drag ratio? Assume a,=0.106/deg, Cdoand e =0.92.0.0043,%3DFor a certain airfoil section, the pitching-moment coefficient about 0.33chord behind the leading edge varies with C, as shown in Table P2.1.1.2

Given Data The weight of the plane is: W=20000 N The area of the plane is: A=30 m2 Aspect ratio is:…

Answered: A flying wing weighing 20,000 N has a…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

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A flying wing weighing 20,000 N has a NACA 65‐418 airfoil section, an area of 30 m2, and an aspect ratio of 5.0. Determine the angle of attack for a sea‐level flight at 60 m/s. What is the lift‐to drag ratio? Assume that the nominal airfoil lift curve slope a0 = 0.106/deg̊, the profile drag CD0 = 0.0043 and e = 0.92.

Problems
1.1 A flying wing weighing 20,000 N has a NACA 653-418 airfoil section, area
of 30 m2, and an aspect ratio 5.0. Determine the angle of attack for a sea level flight
at 60 m/s. What is the lift-to-drag ratio? Assume a,=0.106/deg, Cdo
and e =0.92.
0.0043,
%3D
For a certain airfoil section, the pitching-moment coefficient about 0.33
chord behind the leading edge varies with C, as shown in Table P2.1.
1.2

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