Overall Skin-Friction Drag Coefficient for Incompressible Flow Calculator

✖Reynolds number using chord length, where the length is usually the chord length of an airfoil or the chord length of a wing. The chord length of a wing may vary from root to tip.ⓘ Reynolds number using chord length [Re_c]

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✖Overall Skin-friction Drag Coefficient is an important dimensionless parameter in boundary-layer flows. It specifies the fraction of the local dynamic pressure.ⓘ Overall Skin-Friction Drag Coefficient for Incompressible Flow [C_f]

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Overall Skin-Friction Drag Coefficient for Incompressible Flow

Formula

`"C"_{"f"} = 0.02667/("Re"_{"c"})^0.139`

Example

`"0.009272"=0.02667/("2000")^0.139`

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Overall Skin-Friction Drag Coefficient for Incompressible Flow Solution

STEP 0: Pre-Calculation Summary

Formula Used

Overall Skin-friction Drag Coefficient = 0.02667/(Reynolds number using chord length)^0.139
C_f = 0.02667/(Re_c)^0.139
This formula uses 2 Variables

Variables Used

Overall Skin-friction Drag Coefficient - Overall Skin-friction Drag Coefficient is an important dimensionless parameter in boundary-layer flows. It specifies the fraction of the local dynamic pressure.
Reynolds number using chord length - Reynolds number using chord length, where the length is usually the chord length of an airfoil or the chord length of a wing. The chord length of a wing may vary from root to tip.

STEP 1: Convert Input(s) to Base Unit

Reynolds number using chord length: 2000 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_f = 0.02667/(Re_c)^0.139 --> 0.02667/(2000)^0.139

Evaluating ... ...

C_f = 0.00927213713649144

STEP 3: Convert Result to Output's Unit

0.00927213713649144 --> No Conversion Required

FINAL ANSWER

0.00927213713649144 ≈ 0.009272 <-- Overall Skin-friction Drag Coefficient

(Calculation completed in 00.004 seconds)

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Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Flat Plate for Viscous Flow Case » Reference Temperature Method » Overall Skin-Friction Drag Coefficient for Incompressible Flow

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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PSG College of Technology (PSGCT), Coimbatore

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< 15 Reference Temperature Method Calculators

Mach Number at Reference Temperature

Go Mach Number = sqrt((Reference temperature/Static Temperature-(1+0.58*(Wall Temperature/Static Temperature-1)))/0.032)

Wall Temperature using Reference Temperature

Go Wall Temperature = Static Temperature/0.588*(Reference temperature/Static Temperature-(1+0.032*Mach Number^2))+1

Reference Temperature Equation

Go Reference temperature = Static Temperature*(1+0.032*Mach Number^2+0.58*(Wall Temperature/Static Temperature-1))

Static Velocity of Plate using Chord Length for Flat Plate Case

Go Static Velocity = (Reynolds number using chord length*Static Viscosity)/(Static density*Chord Length)

Static Density of Plate using Chord Length for Flat Plate Case

Go Static density = (Reynolds number using chord length*Static Viscosity)/(Static Velocity*Chord Length)

Chord Length for Flat Plate Case

Go Chord Length = (Reynolds number using chord length*Static Viscosity)/(Static Velocity*Static density)

Static Viscosity of Plate using Chord Length for Flat Plate Case

Go Static Viscosity = Static density*Static Velocity*Chord Length/Reynolds number using chord length

Reynolds Number for Chord Length

Go Reynolds number using chord length = Static density*Static Velocity*Chord Length/Static Viscosity

Stanton Number Obtained from Classical Theory

Go Stanton Number = 0.332/sqrt(Local Reynolds Number)*Prandtl Number^(-2/3)

Overall Skin-Friction Drag Coefficient

Go Overall Skin-friction Drag Coefficient = 1.328/sqrt(Reynolds number using chord length)

Overall Skin-Friction Drag Coefficient for Incompressible Flow

Go Overall Skin-friction Drag Coefficient = 0.02667/(Reynolds number using chord length)^0.139

Reynolds Number for Chord Length using Overall Skin-Friction Drag Coefficient

Go Reynolds number using chord length = (1.328/Overall Skin-friction Drag Coefficient)^2

Local Turbulent Skin-Friction Coefficient for Incompressible Flow

Go Local Skin-Friction Coefficient = 0.02296/(Local Reynolds Number^0.139)

Local Reynolds Number

Go Local Reynolds Number = (0.664^2)/Local Skin-Friction Coefficient^2

Turbulent Flat-Plate Skin-Friction Coefficient

Go Skin friction coefficient = 0.0592/(Local Reynolds Number)^0.2

Overall Skin-Friction Drag Coefficient for Incompressible Flow Formula

Overall Skin-friction Drag Coefficient = 0.02667/(Reynolds number using chord length)^0.139
C_f = 0.02667/(Re_c)^0.139

What is a local Reynolds number?

Based on these observations and the energy equation of a disturbed fluid element, a local Reynolds number Re L is derived to represent the maximum ratio of the energy supplement to the energy dissipation in a cross-section.

How to Calculate Overall Skin-Friction Drag Coefficient for Incompressible Flow?

Overall Skin-Friction Drag Coefficient for Incompressible Flow calculator uses Overall Skin-friction Drag Coefficient = 0.02667/(Reynolds number using chord length)^0.139 to calculate the Overall Skin-friction Drag Coefficient, Overall skin-friction drag coefficient for incompressible flow formula is defined as the function of a constant and Reynolds number of the chord length of the plate. Overall Skin-friction Drag Coefficient is denoted by C_f symbol.

How to calculate Overall Skin-Friction Drag Coefficient for Incompressible Flow using this online calculator? To use this online calculator for Overall Skin-Friction Drag Coefficient for Incompressible Flow, enter Reynolds number using chord length (Re_c) and hit the calculate button. Here is how the Overall Skin-Friction Drag Coefficient for Incompressible Flow calculation can be explained with given input values -> 0.009272 = 0.02667/(2000)^0.139.

FAQ

What is Overall Skin-Friction Drag Coefficient for Incompressible Flow?

Overall skin-friction drag coefficient for incompressible flow formula is defined as the function of a constant and Reynolds number of the chord length of the plate and is represented as C_f = 0.02667/(Re_c)^0.139 or Overall Skin-friction Drag Coefficient = 0.02667/(Reynolds number using chord length)^0.139. Reynolds number using chord length, where the length is usually the chord length of an airfoil or the chord length of a wing. The chord length of a wing may vary from root to tip.

How to calculate Overall Skin-Friction Drag Coefficient for Incompressible Flow?

Overall skin-friction drag coefficient for incompressible flow formula is defined as the function of a constant and Reynolds number of the chord length of the plate is calculated using Overall Skin-friction Drag Coefficient = 0.02667/(Reynolds number using chord length)^0.139. To calculate Overall Skin-Friction Drag Coefficient for Incompressible Flow, you need Reynolds number using chord length (Re_c). With our tool, you need to enter the respective value for Reynolds number using chord length and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Overall Skin-friction Drag Coefficient?

In this formula, Overall Skin-friction Drag Coefficient uses Reynolds number using chord length. We can use 1 other way(s) to calculate the same, which is/are as follows -

Overall Skin-friction Drag Coefficient = 1.328/sqrt(Reynolds number using chord length)

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