Q. 2: Method Planform Design You are to design candidate wings for a sport RC electric aircraft to the following requirements: density: p = 1.2 kg/m³ speed: V = 13.4 mph = 6 m/s lift: L = 11 oz = 3.0 N span: b = 63 in = 1.6 m Assume an elliptic load distribution [(y) = To√/1-(2y/b)² for each of the design cases below. Assume de₂/da = 2 for the wing airfoils. Assume the wing reference line (e.g. fuselage axis) is aligned with the flight direction, so that a = 0°. 2.1) Baseline elliptical wing: Assume a spanwise-constant ce = 0.8. a) (Elliptic) Determine the chord distribution c(y) and sketch the planform. b) (Elliptic) Determine Caero (y). c) (Elliptic) What will ageom (y) look like if the same cambered airfoil is used all across the span? d) (Elliptic) Determine the induced drag for this wing? What is the lift-to-drag ratio?

Q. 2: Method Planform Design You are to design candidate wings for a sport RC electric aircraft to the following requirements: density: p = 1.2 kg/m³ speed: V = 13.4 mph = 6 m/s lift: L = 11 oz = 3.0 N span: b = 63 in = 1.6 m Assume an elliptic load distribution [(y) = To√/1-(2y/b)² for each of the design cases below. Assume de₂/da = 2 for the wing airfoils. Assume the wing reference line (e.g. fuselage axis) is aligned with the flight direction, so that a = 0°. 2.1) Baseline elliptical wing: Assume a spanwise-constant ce = 0.8. a) (Elliptic) Determine the chord distribution c(y) and sketch the planform. b) (Elliptic) Determine Caero (y). c) (Elliptic) What will ageom (y) look like if the same cambered airfoil is used all across the span? d) (Elliptic) Determine the induced drag for this wing? What is the lift-to-drag ratio?

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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Concept explainers

Properties of Fluids

The term fluid represents a type of substance that can easily change its shape under any external pressure/force and can flow. Fluids can acquire any shape in which it is stored and can resist normal stresses but cannot resist shear stress in rest condition. Whenever external shear stress is applied to fluids, it starts to flow. The fluids may be liquid or gas. Example- water, air, etc.

Question

Q. 2: Method Planform Design
You are to design candidate wings for a sport RC electric aircraft to the following requirements:
density: p= 1.2 kg/m³
speed:
lift:
V. = 13.4 mph = 6 m/s
L = 11 oz = 3.0N
span:
b = 63 in = 1.6 m
Assume an elliptic load distribution I(y) = ToV1- (2y/b)² for each of the design cases below.
Assume de /da = 2ñ for the wing airfoils. Assume the wing reference line (e.g. fuselage axis) is
aligned with the flight direction, so that a = 0°.
2.1) Baseline elliptical wing: Assume a spanwise-constant c = 0.8.
a) (Elliptic) Determine the chord distribution c(y) and sketch the planform.
b) (Elliptic) Determine agero(y).
c) (Elliptic) What will ageom (y) look like if the same cambered airfoil is used all across the
span?
d) (Elliptic) Determine the induced drag for this wing? What is the lift-to-drag ratio?

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Step 1: Determine the chord distribution, The angle of attack distribution and the induced drag.

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Step 2: Calculate the chord distribution c(y).

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Step 3: Calculate the angle of attack distribution, for cambered airfoil.

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Step 4: calculate the induced drag.

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Step 5: calculate lift to drag ratio

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