Credits

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
Kaki Varun Krishna has created this Calculator and 25+ more calculators!
Defence institute of advanced technology (DRDO) (DIAT), pune
Abhinav Gupta has verified this Calculator and 8 more calculators!

Taper Ratio of Airfoil Solution

STEP 0: Pre-Calculation Summary
Formula Used
Taper_ratio = Tip_chordlength/Root_chordlength
λ = Ctip/Croot
This formula uses 2 Variables
Variables Used
Tip_chordlength - Tip_chordlength, measured parallel to the plane of symmetry, and at points where straight leading or trailing edges meet the curvature at the tip. (Measured in Meter)
Root_chordlength - Root_chordlength is the chord length is greatest where the wing joins the aircraft's fuselage. (Measured in Meter)
STEP 1: Convert Input(s) to Base Unit
Tip_chordlength: 2 Meter --> 2 Meter No Conversion Required
Root_chordlength: 7 Meter --> 7 Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
λ = Ctip/Croot --> 2/7
Evaluating ... ...
λ = 0.285714285714286
STEP 3: Convert Result to Output's Unit
0.285714285714286 --> No Conversion Required
FINAL ANSWER
0.285714285714286 <-- Taper_ratio
(Calculation completed in 00.016 seconds)

3 Aircraft Design Calculators

Battery Weight Fraction
Battery Weight Fraction = (Range of aircraft/(Battery Specific Energy Capacity*3600* Efficiency*(1/Acceleration Due To Gravity)* Maximum Lift to Drag ratio of Aircraft)) Go
Electric power for a Wind Turbine
Electric_power_windturbine = Shaft Power*Efficiency_Generator*Efficiency of transmission Go
Taper Ratio of Airfoil
Taper_ratio = Tip_chordlength/Root_chordlength Go

Taper Ratio of Airfoil Formula

Taper_ratio = Tip_chordlength/Root_chordlength
λ = Ctip/Croot

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_chordlength/Root_chordlength to calculate the Taper_ratio, Taper Ratio of Airfoil is defined as ratio of the tip chord to the root chord. 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_chordlength (Ctip) & Root_chordlength (Croot) and hit the calculate button. Here is how the Taper Ratio of Airfoil calculation can be explained with given input values -> 0.285714 = 2/7.

FAQ

What is Taper Ratio of Airfoil?
Taper Ratio of Airfoil is defined as ratio of the tip chord to the root chord and is represented as λ = Ctip/Croot or Taper_ratio = Tip_chordlength/Root_chordlength. Tip_chordlength, measured parallel to the plane of symmetry, and at points where straight leading or trailing edges meet the curvature at the tip & Root_chordlength is the chord length is greatest where the wing joins the aircraft's fuselage.
How to calculate Taper Ratio of Airfoil?
Taper Ratio of Airfoil is defined as ratio of the tip chord to the root chord is calculated using Taper_ratio = Tip_chordlength/Root_chordlength. To calculate Taper Ratio of Airfoil, you need Tip_chordlength (Ctip) & Root_chordlength (Croot). With our tool, you need to enter the respective value for Tip_chordlength & Root_chordlength and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!