Aspect Ratio of Wing Solution

STEP 0: Pre-Calculation Summary
Formula Used
Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area
ARw = bW^2/Swet
This formula uses 3 Variables
Variables Used
Aspect Ratio in Lateral Plane - Aspect ratio in Lateral Plane is the ratio of the span to the chord of an airplane wing.
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.
Aircraft Wetted Area - (Measured in Square Meter) - The Aircraft Wetted Area is the surface area that interacts with the working fluid or gas.
STEP 1: Convert Input(s) to Base Unit
Lateral Plane Span: 15.3 Meter --> 15.3 Meter No Conversion Required
Aircraft Wetted Area: 10.16 Square Meter --> 10.16 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
ARw = bW^2/Swet --> 15.3^2/10.16
Evaluating ... ...
ARw = 23.0403543307087
STEP 3: Convert Result to Output's Unit
23.0403543307087 --> No Conversion Required
FINAL ANSWER
23.0403543307087 23.04035 <-- Aspect Ratio in Lateral Plane
(Calculation completed in 00.004 seconds)

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!

13 Aerodynamic Design Calculators

Aerofoil Thickness for 4 Digit Series
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
Go Thrust-to-Weight Ratio = (Minimum Drag Coefficient/Wing Loading+Lift Induced Drag Constant*(Load Factor/Dynamic Pressure)^2*Wing Loading)*Dynamic Pressure
Span given Induced Drag
Go Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure)
Form Factor given Flat Plate Area
Go Form Factor Drag = (Flat Plate Area)/(Skin Friction Coefficient*Aircraft Wetted Area)
Skin Friction Coefficient given Flat Plate Area
Go Skin Friction Coefficient = Flat Plate Area/(Form Factor Drag*Aircraft Wetted Area)
Wetted Area given Flat Plate Area
Go Aircraft Wetted Area = Flat Plate Area/(Form Factor Drag*Skin Friction Coefficient)
Equivalent Parasite Drag Area
Go Flat Plate Area = Form Factor Drag*Skin Friction Coefficient*Aircraft Wetted Area
Span given Aspect Ratio
Go Lateral Plane Span = sqrt(Aspect Ratio in Lateral Plane*Aircraft Wetted Area)
Gross weight given drag
Go Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient)
Wetted Area given Aspect Ratio
Go Aircraft Wetted Area = Lateral Plane Span^2/Aspect Ratio in Lateral Plane
Aspect Ratio of Wing
Go Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area
Taper Ratio of Airfoil
Go Taper Ratio = Tip Chord Length/Root Chord Length
Tip Speed Ratio with Blade Number
Go Tip Speed Ratio = (4*pi)/Number of Blades

Aspect Ratio of Wing Formula

Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area
ARw = bW^2/Swet

What is aspect ratio?

aspect ratio, in aviation, the ratio of the span to the chord of an airplane wing, the latter being the length of the straight line drawn from the leading to the trailing edge, at right angles to the length of the wing.

How to Calculate Aspect Ratio of Wing?

Aspect Ratio of Wing calculator uses Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area to calculate the Aspect Ratio in Lateral Plane, Aspect Ratio of Wing is defined as the ratio of wingspan to mean chord length the ratio of the lateral plane span to the aircraft wetted area provides a measure of how "spread out" the aircraft is relative to its total surface area. Aspect Ratio in Lateral Plane is denoted by ARw symbol.

How to calculate Aspect Ratio of Wing using this online calculator? To use this online calculator for Aspect Ratio of Wing, enter Lateral Plane Span (bW) & Aircraft Wetted Area (Swet) and hit the calculate button. Here is how the Aspect Ratio of Wing calculation can be explained with given input values -> 23.04035 = 15.3^2/10.16.

FAQ

What is Aspect Ratio of Wing?
Aspect Ratio of Wing is defined as the ratio of wingspan to mean chord length the ratio of the lateral plane span to the aircraft wetted area provides a measure of how "spread out" the aircraft is relative to its total surface area and is represented as ARw = bW^2/Swet or Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area. 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 & The Aircraft Wetted Area is the surface area that interacts with the working fluid or gas.
How to calculate Aspect Ratio of Wing?
Aspect Ratio of Wing is defined as the ratio of wingspan to mean chord length the ratio of the lateral plane span to the aircraft wetted area provides a measure of how "spread out" the aircraft is relative to its total surface area is calculated using Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area. To calculate Aspect Ratio of Wing, you need Lateral Plane Span (bW) & Aircraft Wetted Area (Swet). With our tool, you need to enter the respective value for Lateral Plane Span & Aircraft Wetted Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!