Taper Ratio of Airfoil Calculator

✖Tip Chord Length, measured parallel to the plane of symmetry, and at points where straight leading or trailing edges meet the curvature at the tip.ⓘ Tip Chord Length [C_tip]			+10% -10%
✖Root Chord Length is the chord length of the root airfoil, which is attached to the fuselage.ⓘ Root Chord Length [C_root]			+10% -10%

✖Taper Ratio is the ratio of the tip chord to the root chord.ⓘ Taper Ratio of Airfoil [Λ]

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Taper Ratio of Airfoil Solution

STEP 0: Pre-Calculation Summary

Formula Used

Taper Ratio = Tip Chord Length/Root Chord Length
Λ = C_tip/C_root
This formula uses 3 Variables

Variables Used

Taper Ratio - Taper Ratio is the ratio of the tip chord to the root chord.
Tip Chord Length - (Measured in Meter) - Tip Chord Length, measured parallel to the plane of symmetry, and at points where straight leading or trailing edges meet the curvature at the tip.
Root Chord Length - (Measured in Meter) - Root Chord Length is the chord length of the root airfoil, which is attached to the fuselage.

STEP 1: Convert Input(s) to Base Unit

Tip Chord Length: 3 Meter --> 3 Meter No Conversion Required
Root Chord Length: 7 Meter --> 7 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Λ = C_tip/C_root --> 3/7

Evaluating ... ...

Λ = 0.428571428571429

STEP 3: Convert Result to Output's Unit

0.428571428571429 --> No Conversion Required

FINAL ANSWER

0.428571428571429 ≈ 0.428571 <-- Taper Ratio

(Calculation completed in 00.004 seconds)

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Created by Kaki Varun Krishna

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad

Kaki Varun Krishna has created this Calculator and 25+ more calculators!

Verified by Abhinav Gupta

Defence institute of advanced technology (DRDO) (DIAT), pune

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

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Taper Ratio of Airfoil Formula

LaTeX Go

Taper Ratio = Tip Chord Length/Root Chord Length
Λ = C_tip/C_root

How does Taper affect Lift?

Tapering causes a decrease in drag (most effective at high speeds) and an increase in lift. There is also a structural benefit due to a saving in weight of the wing.

How to Calculate Taper Ratio of Airfoil?

Taper Ratio of Airfoil calculator uses Taper Ratio = Tip Chord Length/Root Chord Length to calculate the Taper Ratio, The Taper Ratio of Airfoil refers to the ratio of the chord length at the wing root (base) to the chord length at the wing tip,it's a geometric parameter that describes how the width of the wing changes from the base to the tip. Taper Ratio is denoted by Λ symbol.

How to calculate Taper Ratio of Airfoil using this online calculator? To use this online calculator for Taper Ratio of Airfoil, enter Tip Chord Length (C_tip) & Root Chord Length (C_root) and hit the calculate button. Here is how the Taper Ratio of Airfoil calculation can be explained with given input values -> 0.428571 = 3/7.

FAQ

What is Taper Ratio of Airfoil?

The Taper Ratio of Airfoil refers to the ratio of the chord length at the wing root (base) to the chord length at the wing tip,it's a geometric parameter that describes how the width of the wing changes from the base to the tip and is represented as Λ = C_tip/C_root or Taper Ratio = Tip Chord Length/Root Chord Length. Tip Chord Length, measured parallel to the plane of symmetry, and at points where straight leading or trailing edges meet the curvature at the tip & Root Chord Length is the chord length of the root airfoil, which is attached to the fuselage.

How to calculate Taper Ratio of Airfoil?

The Taper Ratio of Airfoil refers to the ratio of the chord length at the wing root (base) to the chord length at the wing tip,it's a geometric parameter that describes how the width of the wing changes from the base to the tip is calculated using Taper Ratio = Tip Chord Length/Root Chord Length. To calculate Taper Ratio of Airfoil, you need Tip Chord Length (C_tip) & Root Chord Length (C_root). With our tool, you need to enter the respective value for Tip Chord Length & Root Chord Length and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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