Reynolds Number for Airfoil Calculator

✖Density of Fluid is defined as the mass of fluid per unit volume of the said fluid.ⓘ Density of Fluid [ρ_f]			+10% -10%
✖Flow Velocity refers to the speed at which a fluid moves through a particular area or space.ⓘ Flow Velocity [V_flow]			+10% -10%
✖The Chord Length of Airfoil is the distance from the leading edge to the trailing edge.ⓘ Chord Length of Airfoil [c]			+10% -10%
✖The Dynamic Viscosity of a fluid is the measure of its resistance to flow when an external force is applied.ⓘ Dynamic Viscosity [μ]			+10% -10%

✖The Reynolds Number is the ratio of inertial forces to viscous forces. The Reynolds number is used to determine whether a fluid is laminar or turbulent.ⓘ Reynolds Number for Airfoil [Re]

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Reynolds Number for Airfoil Solution

STEP 0: Pre-Calculation Summary

Formula Used

Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity
Re = (ρ_f*V_flow*c)/μ
This formula uses 5 Variables

Variables Used

Reynolds Number - The Reynolds Number is the ratio of inertial forces to viscous forces. The Reynolds number is used to determine whether a fluid is laminar or turbulent.
Density of Fluid - (Measured in Kilogram per Cubic Meter) - Density of Fluid is defined as the mass of fluid per unit volume of the said fluid.
Flow Velocity - (Measured in Meter per Second) - Flow Velocity refers to the speed at which a fluid moves through a particular area or space.
Chord Length of Airfoil - (Measured in Meter) - The Chord Length of Airfoil is the distance from the leading edge to the trailing edge.
Dynamic Viscosity - (Measured in Pascal Second) - The Dynamic Viscosity of a fluid is the measure of its resistance to flow when an external force is applied.

STEP 1: Convert Input(s) to Base Unit

Density of Fluid: 170.194007 Kilogram per Cubic Meter --> 170.194007 Kilogram per Cubic Meter No Conversion Required
Flow Velocity: 39.95440334 Meter per Second --> 39.95440334 Meter per Second No Conversion Required
Chord Length of Airfoil: 0.45 Meter --> 0.45 Meter No Conversion Required
Dynamic Viscosity: 10.2 Poise --> 1.02 Pascal Second (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Re = (ρ_f*V_flow*c)/μ --> (170.194007*39.95440334*0.45)/1.02

Evaluating ... ...

Re = 3000.0000007627

STEP 3: Convert Result to Output's Unit

3000.0000007627 --> No Conversion Required

FINAL ANSWER

3000.0000007627 ≈ 3000 <-- Reynolds Number

(Calculation completed in 00.004 seconds)

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Created by Vishal Anand

Indian Institute of Technology Kharagpur (IIT KGP), Kharagpur

Vishal Anand has created this Calculator and 7 more calculators!

Verified by Ojas Kulkarni

Sardar Patel College of Engineering (SPCE), Mumbai

Ojas Kulkarni has verified this Calculator and 8 more calculators!

< Computational Fluid Dyanmics Calculators

Drag on Airfoil

LaTeX 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

LaTeX 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

LaTeX Go Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity

Friction Velocity for Airfoil

LaTeX Go Friction Velocity For Airfoil = (Wall Shear Stress For Airfoil/Density of Air)^0.5

Reynolds Number for Airfoil Formula

LaTeX Go

Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity
Re = (ρ_f*V_flow*c)/μ

What is the effect of Reynolds number on airfoil?

The higher the Reynolds number, the lesser the viscosity plays a role in the flow around the airfoil.With increasing Reynolds number the boundary layer gets thinner, which results in a lower drag. Increasing the Reynolds number also has a destabilizing effect on the boundary layer flow, which results in the transition location moving toward the leading edge, leading to a turbulent boundary layer over a longer part of the airfoil surface. The net effect is a lower drag but a smaller low-drag range of angles of attack. This implies that the maximum lift–drag ratio will increase, but that the design lift coefficient will decrease.

How to Calculate Reynolds Number for Airfoil?

Reynolds Number for Airfoil calculator uses Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity to calculate the Reynolds Number, The Reynolds Number for airfoil is a dimensionless value that is used to determine whether the fluid is exhibiting laminar flow (R less than 2300) or turbulent flow (R greater than 4000). Reynolds Number is denoted by Re symbol.

How to calculate Reynolds Number for Airfoil using this online calculator? To use this online calculator for Reynolds Number for Airfoil, enter Density of Fluid (ρ_f), Flow Velocity (V_flow), Chord Length of Airfoil (c) & Dynamic Viscosity (μ) and hit the calculate button. Here is how the Reynolds Number for Airfoil calculation can be explained with given input values -> 3000 = (170.194007*39.95440334*0.45)/1.02.

FAQ

What is Reynolds Number for Airfoil?

The Reynolds Number for airfoil is a dimensionless value that is used to determine whether the fluid is exhibiting laminar flow (R less than 2300) or turbulent flow (R greater than 4000) and is represented as Re = (ρ_f*V_flow*c)/μ or Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity. Density of Fluid is defined as the mass of fluid per unit volume of the said fluid, Flow Velocity refers to the speed at which a fluid moves through a particular area or space, The Chord Length of Airfoil is the distance from the leading edge to the trailing edge & The Dynamic Viscosity of a fluid is the measure of its resistance to flow when an external force is applied.

How to calculate Reynolds Number for Airfoil?

The Reynolds Number for airfoil is a dimensionless value that is used to determine whether the fluid is exhibiting laminar flow (R less than 2300) or turbulent flow (R greater than 4000) is calculated using Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity. To calculate Reynolds Number for Airfoil, you need Density of Fluid (ρ_f), Flow Velocity (V_flow), Chord Length of Airfoil (c) & Dynamic Viscosity (μ). With our tool, you need to enter the respective value for Density of Fluid, Flow Velocity, Chord Length of Airfoil & Dynamic Viscosity 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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