Induced Drag Calculator

Induced Drag Calculator calculator can be used to calculate the induced drag of an aircraft wing based on its geometric properties and flight conditions.

Input Parameters

Calculation Results

Calculation Formula

Induced Drag (Di) = 0.5 × ρ × V² × (CL² / AR)

Where:
Di = Induced Drag (N)
ρ = Air Density (kg/m³)
V = Flight Velocity (m/s)
CL = Lift Coefficient
AR = Aspect Ratio

Induced Drag Calculator Calculator Usage Guide

Learn how to use the Induced Drag Calculator calculator and its working principles

How to Use the Calculator

  1. Enter the Wing Area in square meters (m²)
  2. Enter the Aspect Ratio (ratio of wingspan to mean chord)
  3. Enter the Lift Coefficient (CL)
  4. Enter the Air Density in kg/m³ (standard sea level is 1.225 kg/m³)
  5. Click the "Calculate" button to compute the induced drag and drag coefficient

Understanding Induced Drag

Induced drag is an aerodynamic force that occurs when an aircraft generates lift. It is a byproduct of lift and increases as the angle of attack increases or as the aspect ratio decreases.

The formula used in this calculator is:

Di = 0.5 × ρ × V² × (CL² / AR)

Where:

  • Di = Induced Drag (Newtons, N)
  • ρ = Air Density (kg/m³)
  • V = Flight Velocity (m/s)
  • CL = Lift Coefficient
  • AR = Aspect Ratio

Applications

This calculator is useful for:

  • Aircraft designers to optimize wing geometry
  • Pilots to understand performance limitations
  • Aerospace engineers in performance analysis