Drag on Airfoil Solution

STEP 0: Pre-Calculation Summary
Formula Used
Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil)
D = N*sin(α°)+A*cos(α°)
This formula uses 2 Functions, 4 Variables
Functions Used
sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)
cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(Angle)
Variables Used
Drag on Airfoil - (Measured in Newton) - Drag on Airfoil is the component of Resultant Force acting on airfoil parallel to freestream velocity.
Normal Force on Airfoil - (Measured in Newton) - Normal Force on airfoil is component of Resultant force acting on airfoil perpendicular to chord.
Angle of Attack of Airfoil - (Measured in Radian) - The Angle of Attack of Airfoil is the angle between freestream velocity and chord of the airfoil.
Axial Force on airfoil - (Measured in Newton) - Axial Force on airfoil is component of Resultant force acting on airfoil parallel to chord.
STEP 1: Convert Input(s) to Base Unit
Normal Force on Airfoil: 11 Newton --> 11 Newton No Conversion Required
Angle of Attack of Airfoil: 8 Degree --> 0.13962634015952 Radian (Check conversion here)
Axial Force on airfoil: 20 Newton --> 20 Newton No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
D = N*sin(α°)+A*cos(α°) --> 11*sin(0.13962634015952)+20*cos(0.13962634015952)
Evaluating ... ...
D = 21.3362654853919
STEP 3: Convert Result to Output's Unit
21.3362654853919 Newton --> No Conversion Required
FINAL ANSWER
21.3362654853919 21.33627 Newton <-- Drag on Airfoil
(Calculation completed in 00.020 seconds)

Credits

Created by Vishal Anand
Indian Institute of Technology Kharagpur (IIT KGP), Kharagpur
Vishal Anand has created this Calculator and 7 more calculators!
Verified by Ayush Singh
Gautam Buddha University (GBU), Greater Noida
Ayush Singh has verified this Calculator and 100+ more calculators!

7 Computational Fluid Dyanmics Calculators

Drag on Airfoil
Go Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil)
Lift on Airfoil
Go Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on airfoil*sin(Angle of Attack of Airfoil)
Reynolds Number for Airfoil
Go Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity
Y Plus
Go Y Plus = First layer height*Density of Air*Friction Velocity for Airfoil/Kinematic Viscosity
Wall Shear Stress for Airfoil
Go Wall Shear Stress for Airfoil = 0.5*Skin friction coefficient*Flow Velocity*Density of Air
Friction Velocity for Airfoil
Go Friction Velocity for Airfoil = (Wall Shear Stress for Airfoil/Density of Air)^0.5
Skin Friction Coefficient
Go Skin friction coefficient = (2*log10(Reynolds Number)-0.65)^(-2.30)

Drag on Airfoil Formula

Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil)
D = N*sin(α°)+A*cos(α°)

How to Calculate Drag on Airfoil?

Drag on Airfoil calculator uses Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil) to calculate the Drag on Airfoil, The Drag on airfoil is defined as the component of resultant force acting on airfoil in the direction of freestream velocity. Drag on Airfoil is denoted by D symbol.

How to calculate Drag on Airfoil using this online calculator? To use this online calculator for Drag on Airfoil, enter Normal Force on Airfoil (N), Angle of Attack of Airfoil (α°) & Axial Force on airfoil (A) and hit the calculate button. Here is how the Drag on Airfoil calculation can be explained with given input values -> 21.33627 = 11*sin(0.13962634015952)+20*cos(0.13962634015952).

FAQ

What is Drag on Airfoil?
The Drag on airfoil is defined as the component of resultant force acting on airfoil in the direction of freestream velocity and is represented as D = N*sin(α°)+A*cos(α°) or Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil). Normal Force on airfoil is component of Resultant force acting on airfoil perpendicular to chord, The Angle of Attack of Airfoil is the angle between freestream velocity and chord of the airfoil & Axial Force on airfoil is component of Resultant force acting on airfoil parallel to chord.
How to calculate Drag on Airfoil?
The Drag on airfoil is defined as the component of resultant force acting on airfoil in the direction of freestream velocity is calculated using Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil). To calculate Drag on Airfoil, you need Normal Force on Airfoil (N), Angle of Attack of Airfoil (α°) & Axial Force on airfoil (A). With our tool, you need to enter the respective value for Normal Force on Airfoil, Angle of Attack of Airfoil & Axial Force on airfoil 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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