FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Induced Drag for Wings having Elliptic Lift Distribution Formula

GoInduced Drag Given Span Efficiency Factor Formula

Fx Copy

LaTeX Copy

Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing. Check FAQs

D i = \frac{{F L}^{2}}{3.14 \cdot q \cdot {b W}^{2}}

D_i - Induced Drag?F_L - Lift Force?q - Dynamic Pressure?b_W - Lateral Plane Span?

Induced Drag for Wings having Elliptic Lift Distribution Example

With values

With units

Only example

Here is how the Induced Drag for Wings having Elliptic Lift Distribution equation looks like with Values.

Here is how the Induced Drag for Wings having Elliptic Lift Distribution equation looks like with Units.

Here is how the Induced Drag for Wings having Elliptic Lift Distribution equation looks like.

0.0045 = \frac{{2.926}^{2}}{3.14 \cdot 2.667 \cdot 15^{2}}

0.0045N = \frac{{2.926N}^{2}}{3.14 \cdot 2.667Pa \cdot {15m}^{2}}

0.0045 = \frac{{2.926}^{2}}{3.14 \cdot 2.667 \cdot 15^{2}}

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aircraft Mechanics » fx Induced Drag for Wings having Elliptic Lift Distribution

Induced Drag for Wings having Elliptic Lift Distribution Solution

Follow our step by step solution on how to calculate Induced Drag for Wings having Elliptic Lift Distribution?

FIRST Step Consider the formula

D i = \frac{{F L}^{2}}{3.14 \cdot q \cdot {b W}^{2}}

Next Step Substitute values of Variables

∴

D i = \frac{{2.926N}^{2}}{3.14 \cdot 2.667Pa \cdot {15m}^{2}}

Next Step Prepare to Evaluate

∴

D i = \frac{{2.926}^{2}}{3.14 \cdot 2.667 \cdot 15^{2}}

Next Step Evaluate

∴

D i = 0.00454373988814031N

LAST Step Rounding Answer

∴

D i = 0.0045N

Induced Drag for Wings having Elliptic Lift Distribution Formula Elements

Variables

Induced Drag

Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing.

Symbol: D_i

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Induced Drag

Lift Force

Lift force is the component of the total force acting on a body that is perpendicular to the direction of the fluid flow.

Symbol: F_L

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Lift Force

Dynamic Pressure

Dynamic pressure, also referred to as velocity pressure, is a specific type of pressure associated with the kinetic energy per unit volume of a moving fluid.

Symbol: q

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Dynamic Pressure

Lateral Plane Span

Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.

Symbol: b_W

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Lateral Plane Span

Other Formulas to find Induced Drag

Go Induced Drag Given Span Efficiency Factor

D i = C D \cdot ρ \cdot v^{2} \cdot \frac{S ref}{2}

Other formulas in Lift and Drag Polar category

Go Drag Coefficient for given parasite drag coefficient

C D = C D,e + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Go Drag Coefficient for given zero-lift drag coefficient

C D = C D,0 + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Go Coefficient of Drag due to lift

C D,i = \frac{{C L}^{2}}{π \cdot e oswald \cdot AR}

Go Parasite Drag Coefficient at zero lift

C D,0 = C D - C D,i

How to Evaluate Induced Drag for Wings having Elliptic Lift Distribution?

Induced Drag for Wings having Elliptic Lift Distribution evaluator uses Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2) to evaluate the Induced Drag, Induced Drag for Wings having Elliptic Lift Distribution is a measure of the drag force that occurs when a wing produces lift, characterized by an elliptical distribution of lift across the span, and is influenced by the lift force, dynamic pressure, and lateral plane span of the wing. Induced Drag is denoted by D_i symbol.

How to evaluate Induced Drag for Wings having Elliptic Lift Distribution using this online evaluator? To use this online evaluator for Induced Drag for Wings having Elliptic Lift Distribution, enter Lift Force (F_L), Dynamic Pressure (q) & Lateral Plane Span (b_W) and hit the calculate button.

FAQs on Induced Drag for Wings having Elliptic Lift Distribution

What is the formula to find Induced Drag for Wings having Elliptic Lift Distribution?

The formula of Induced Drag for Wings having Elliptic Lift Distribution is expressed as Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2). Here is an example- 0.004544 = (2.926^2)/(3.14*2.667*15^2).

How to calculate Induced Drag for Wings having Elliptic Lift Distribution?

With Lift Force (F_L), Dynamic Pressure (q) & Lateral Plane Span (b_W) we can find Induced Drag for Wings having Elliptic Lift Distribution using the formula - Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2).

What are the other ways to Calculate Induced Drag?

Here are the different ways to Calculate Induced Drag-

Induced Drag=Drag Coefficient*Density of Material*Velocity^2*Reference Area/2

Can the Induced Drag for Wings having Elliptic Lift Distribution be negative?

Yes, the Induced Drag for Wings having Elliptic Lift Distribution, measured in Force can be negative.

Which unit is used to measure Induced Drag for Wings having Elliptic Lift Distribution?

Induced Drag for Wings having Elliptic Lift Distribution is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Induced Drag for Wings having Elliptic Lift Distribution can be measured.

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Induced Drag for Wings having Elliptic Lift Distribution Formula

​GoInduced Drag Given Span Efficiency Factor Formula

Induced Drag for Wings having Elliptic Lift Distribution Example

Induced Drag for Wings having Elliptic Lift Distribution Solution

Induced Drag for Wings having Elliptic Lift Distribution Formula Elements

Other Formulas to find Induced Drag

Other formulas in Lift and Drag Polar category

How to Evaluate Induced Drag for Wings having Elliptic Lift Distribution?

FAQs on Induced Drag for Wings having Elliptic Lift Distribution

Variable Name

GoInduced Drag Given Span Efficiency Factor Formula