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Span given Induced Drag Formula

GoSpan given Aspect Ratio Formula

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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. Check FAQs

b W = \frac{F L}{\sqrt{π \cdot D i \cdot q}}

b_W - Lateral Plane Span?F_L - Lift Force?D_i - Induced Drag?q - Dynamic Pressure?π - Archimedes' constant?

Span given Induced Drag Example

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Here is how the Span given Induced Drag equation looks like with Values.

Here is how the Span given Induced Drag equation looks like with Units.

Here is how the Span given Induced Drag equation looks like.

15.0786 = \frac{110}{\sqrt{3.1416 \cdot 8.47 \cdot 2}}

15.0786m = \frac{110N}{\sqrt{3.1416 \cdot 8.47N \cdot 2Pa}}

15.0786 = \frac{110}{\sqrt{3.1416 \cdot 8.47 \cdot 2}}

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Span given Induced Drag Solution

Follow our step by step solution on how to calculate Span given Induced Drag?

FIRST Step Consider the formula

b W = \frac{F L}{\sqrt{π \cdot D i \cdot q}}

Next Step Substitute values of Variables

∴

b W = \frac{110N}{\sqrt{π \cdot 8.47N \cdot 2Pa}}

Next Step Substitute values of Constants

∴

b W = \frac{110N}{\sqrt{3.1416 \cdot 8.47N \cdot 2Pa}}

Next Step Prepare to Evaluate

∴

b W = \frac{110}{\sqrt{3.1416 \cdot 8.47 \cdot 2}}

Next Step Evaluate

∴

b W = 15.0786008773027m

LAST Step Rounding Answer

∴

b W = 15.0786m

Span given Induced Drag Formula Elements

Variables

Constants

Functions

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

Lift Force

Lift Force is the aerodynamic force exerted on an object, such as an aircraft wing, perpendicular to the oncoming airflow.

Symbol: F_L

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Lift Force

Induced Drag

Induced Drag is a type of aerodynamic drag that occurs as a result of the lift production in an aircraft. It is associated with the creation of vortices at the wingtips, leading to a downwash of air.

Symbol: D_i

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Induced Drag

Dynamic Pressure

Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.

Symbol: q

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Dynamic Pressure

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

sqrt

A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number.

Syntax: sqrt(Number)

Other Formulas to find Lateral Plane Span

Go Span given Aspect Ratio

b W = \sqrt{AR w \cdot S wet}

Other formulas in Aerodynamic Design category

Go Aerofoil Thickness for 4 Digit Series

y t = \frac{t \cdot (0.2969 \cdot x^{0.5} - 0.1260 \cdot x - 0.3516 \cdot x^{2} + 0.2843 \cdot x^{3} - 0.1015 \cdot x^{4})}{0.2}

Go Thrust-to-Weight Ratio given Minimum Coefficient of Drag

TW = (\frac{C Dmin}{W S} + k \cdot {(\frac{n}{q})}^{2} \cdot W S) \cdot q

Go Taper Ratio of Airfoil

Λ = \frac{C tip}{C root}

Go Tip Speed Ratio with Blade Number

λ = \frac{4 \cdot π}{N}

How to Evaluate Span given Induced Drag?

Span given Induced Drag evaluator uses Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure) to evaluate the Lateral Plane Span, The Span given Induced Drag formula describes the relationship between the span (b) of an aircraft and the induced drag it experiences during flight. It quantifies the span required to counteract the induced drag force generated by the aircraft's wings. In essence, the formula illustrates how the span influences the aerodynamic efficiency of the aircraft, as a larger span can help reduce induced drag. Lateral Plane Span is denoted by b_W symbol.

How to evaluate Span given Induced Drag using this online evaluator? To use this online evaluator for Span given Induced Drag, enter Lift Force (F_L), Induced Drag (D_i) & Dynamic Pressure (q) and hit the calculate button.

FAQs on Span given Induced Drag

What is the formula to find Span given Induced Drag?

The formula of Span given Induced Drag is expressed as Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure). Here is an example- 15.0786 = 110/sqrt(pi*8.47*2).

How to calculate Span given Induced Drag?

With Lift Force (F_L), Induced Drag (D_i) & Dynamic Pressure (q) we can find Span given Induced Drag using the formula - Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure). This formula also uses Archimedes' constant and Square Root Function function(s).

What are the other ways to Calculate Lateral Plane Span?

Here are the different ways to Calculate Lateral Plane Span-

Lateral Plane Span=sqrt(Aspect Ratio in Lateral Plane*Aircraft Wetted Area)

Can the Span given Induced Drag be negative?

No, the Span given Induced Drag, measured in Length cannot be negative.

Which unit is used to measure Span given Induced Drag?

Span given Induced Drag is usually measured using the Meter[m] for Length. Millimeter[m], Kilometer[m], Decimeter[m] are the few other units in which Span given Induced Drag can be measured.

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Span given Induced Drag Formula

​GoSpan given Aspect Ratio Formula

Span given Induced Drag Example

Span given Induced Drag Solution

Span given Induced Drag Formula Elements

Other Formulas to find Lateral Plane Span

Other formulas in Aerodynamic Design category

How to Evaluate Span given Induced Drag?

FAQs on Span given Induced Drag

Variable Name

GoSpan given Aspect Ratio Formula