Span given Induced Drag Calculator

✖Lift Force is the aerodynamic force exerted on an object, such as an aircraft wing, perpendicular to the oncoming airflow.ⓘ Lift Force [F_L]			+10% -10%
✖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.ⓘ Induced Drag [D_i]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [q]			+10% -10%

✖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.ⓘ Span given Induced Drag [b_W]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Aerodynamic Design Formulas PDF PDF Image

Span given Induced Drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure)
b_W = F_L/sqrt(pi*D_i*q)
This formula uses 1 Constants, 1 Functions, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Functions Used

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., sqrt(Number)

Variables Used

Lateral Plane Span - (Measured in Meter) - 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.
Lift Force - (Measured in Newton) - Lift Force is the aerodynamic force exerted on an object, such as an aircraft wing, perpendicular to the oncoming airflow.
Induced Drag - (Measured in Newton) - 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.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.

STEP 1: Convert Input(s) to Base Unit

Lift Force: 110 Newton --> 110 Newton No Conversion Required
Induced Drag: 8.47 Newton --> 8.47 Newton No Conversion Required
Dynamic Pressure: 2 Pascal --> 2 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

b_W = F_L/sqrt(pi*D_i*q) --> 110/sqrt(pi*8.47*2)

Evaluating ... ...

b_W = 15.0786008773027

STEP 3: Convert Result to Output's Unit

15.0786008773027 Meter --> No Conversion Required

FINAL ANSWER

15.0786008773027 ≈ 15.0786 Meter <-- Lateral Plane Span

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Design » Conceptual Design » Aerospace » Aerodynamic Design » Span given Induced Drag

Credits

Created by Himanshu Sharma

National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

Himanshu Sharma has created this Calculator and 50+ more calculators!

Verified by Kartikay Pandit

National Institute Of Technology (NIT), Hamirpur

Kartikay Pandit has verified this Calculator and 400+ more calculators!

< Aerodynamic Design Calculators

Aerofoil Thickness for 4 Digit Series

LaTeX Go Half Thickness = (Maximum Thickness*(0.2969*Position along the Chord^0.5-0.1260*Position along the Chord-0.3516*Position along the Chord^2+0.2843*Position along the Chord^3-0.1015*Position along the Chord^4))/0.2

Thrust-to-Weight Ratio given Minimum Coefficient of Drag

LaTeX Go Thrust-to-Weight Ratio = (Minimum Drag Coefficient/Wing Loading+Lift Induced Drag Constant*(Load Factor/Dynamic Pressure)^2*Wing Loading)*Dynamic Pressure

Taper Ratio of Airfoil

LaTeX Go Taper Ratio = Tip Chord Length/Root Chord Length

Tip Speed Ratio with Blade Number

LaTeX Go Tip Speed Ratio = (4*pi)/Number of Blades

Span given Induced Drag Formula

LaTeX Go

Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure)
b_W = F_L/sqrt(pi*D_i*q)

What is plane span?

The set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v. Moreover, if u and v are parallel to given plane P, then the plane P is said to be spanned by u and v.

How to Calculate Span given Induced Drag?

Span given Induced Drag calculator uses Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure) to calculate 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 calculate Span given Induced Drag using this online calculator? To use this online calculator for Span given Induced Drag, enter Lift Force (F_L), Induced Drag (D_i) & Dynamic Pressure (q) and hit the calculate button. Here is how the Span given Induced Drag calculation can be explained with given input values -> 15.0786 = 110/sqrt(pi*8.47*2).

FAQ

What is Span given Induced Drag?

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 and is represented as b_W = F_L/sqrt(pi*D_i*q) or Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure). Lift Force is the aerodynamic force exerted on an object, such as an aircraft wing, perpendicular to the oncoming airflow, 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 & Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.

How to calculate Span given Induced Drag?

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 is calculated using Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure). To calculate Span given Induced Drag, you need Lift Force (F_L), Induced Drag (D_i) & Dynamic Pressure (q). With our tool, you need to enter the respective value for Lift Force, Induced Drag & Dynamic Pressure and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Lateral Plane Span?

In this formula, Lateral Plane Span uses Lift Force, Induced Drag & Dynamic Pressure. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

Home

FREE PDFs

🔍 Search