Calculate wing aspect ratio from wingspan and wing area, or solve for span, area and mean chord, with taper ratio, MAC and effective AR.

Full tip-to-tip span and total projected wing planform area.

Output units and aerodynamic scenario

Editable 0.8 illustration. Blank uses 0.8; this model supports e up to 1.2.

Editable 0.4 illustration. Blank uses 0.4; zero gives zero induced drag.

Editable 2ฯ€ illustration. Blank uses 2ฯ€; actual airfoil values differ.

Wing Aspect Ratio Formula

Use full tip-to-tip span and total projected planform area, including both wing halves. Aspect ratio is dimensionless. The calculator also solves span, area or mean geometric chord. Its rectangular and straight-tapered input methods derive area from chords; inverse geometry or span/area alone does not establish mean aerodynamic chord (MAC).

WAR = WSยฒ / A

Variables:

  • WAR is the Wing Aspect Ratio
  • WS is the full tip-to-tip wingspan, in a selected length unit 
  • A is total projected wing planform area, in the square of a consistent length unit; it is not upper-plus-lower skin area 

To calculate geometric aspect ratio, square full span and divide by total planform area after unit conversion. Equivalently, divide span by the mean geometric chord S/b. Individual unit changes convert quantities. Optional coefficient estimates use CDi = CL squared / (pi * e * ARused), with your efficiency, lift coefficient and airfoil-slope inputs; defaults 0.8, 0.4 and 2pi are editable illustrations, not aircraft recommendations. The selectable sweep/winglet scenario uses ARused = AR * cos squared(sweep) * (1 + 1.9 * height/full span). This combined heuristic is illustrative and not a validated universal effective AR or performance prediction. Geometric AR and area remain unchanged.

How to Calculate Wing Aspect Ratio?

The following steps outline how to calculate the Wing Aspect Ratio.

  1. First, determine the total wingspan (ft). 
  2. Next, determine the total wing area (ft^2). 
  3. Next, gather the formula from above = WAR = WS^2 / A.
  4. Finally, calculate the Wing Aspect Ratio.
  5. After inserting the variables and calculating the result, check your answer with the calculator above.

Example Problem : 

Use the following variables as an example problem to test your knowledge.

total wingspan (ft) = 30

total wing area (ft^2) = 250

WAR = WS^2 / A = 30^2 / 250 = 3.6. Mean geometric chord = 250/30 = 8.333333 ft. The coefficient scenario does not change these geometry results.