Skin-Friction Drag for Flat Plate in Viscous Flow Calculator

✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [q]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Skin friction coefficient is an important dimensionless parameter in boundary-layer flows. It specifies the fraction of the local dynamic pressure.ⓘ Skin friction coefficient [c_f]			+10% -10%

✖Skin Friction Drag Force, also known as Friction Drag, is drag caused by the friction of a fluid against the surface of an object that is moving through it.ⓘ Skin-Friction Drag for Flat Plate in Viscous Flow [F_skin]

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Skin-Friction Drag for Flat Plate in Viscous Flow

Formula

`"F"_{"skin"} = "q"*"S"*"c"_{"f"}`

Example

`"36.576N"="10Pa"*"5.08m²"*"0.72"`

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Skin-Friction Drag for Flat Plate in Viscous Flow Solution

STEP 0: Pre-Calculation Summary

Formula Used

Skin Friction Drag Force = Dynamic Pressure*Reference Area*Skin friction coefficient
F_skin = q*S*c_f
This formula uses 4 Variables

Variables Used

Skin Friction Drag Force - (Measured in Newton) - Skin Friction Drag Force, also known as Friction Drag, is drag caused by the friction of a fluid against the surface of an object that is moving through it.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Skin friction coefficient - Skin friction coefficient is an important dimensionless parameter in boundary-layer flows. It specifies the fraction of the local dynamic pressure.

STEP 1: Convert Input(s) to Base Unit

Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Skin friction coefficient: 0.72 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_skin = q*S*c_f --> 10*5.08*0.72

Evaluating ... ...

F_skin = 36.576

STEP 3: Convert Result to Output's Unit

36.576 Newton --> No Conversion Required

FINAL ANSWER

36.576 Newton <-- Skin Friction Drag Force

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 15 Viscous Flow Calculators

Static Velocity Equation using Aerodynamic Heating Equation

Go Static Velocity = Local Heat Transfer Rate/(Static Density*Stanton Number*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Static Density Equation using Aerodynamic Equation

Go Static Density = Local Heat Transfer Rate/(Static Velocity*Stanton Number*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Aerodynamic Heating Equation for Stanton number

Go Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Recovery Factor using Temperature

Go Recovery Factor = (Adiabatic Wall Temperature-Static Temperature)/(Total Temperature-Static Temperature)

Recovery Factor for Flat Plate with Viscous Flow

Go Recovery Factor = (Adiabatic Wall Enthalpy-Static Enthalpy)/(Total Specific Enthalpy-Static Enthalpy)

Adiabatic Wall Enthalpy for Flat Plate

Go Adiabatic Wall Enthalpy = Static Enthalpy+Recovery Factor*(Total Specific Enthalpy-Static Enthalpy)

Drag per Unit Span

Go Drag Force = (0.86*Dynamic Pressure*Distance from Leading Edge)/sqrt(Reynolds Number)

Skin-Friction Drag Coefficient

Go Skin friction coefficient = Skin Friction Drag Force/(Dynamic Pressure*Reference Area)

Skin-Friction Drag for Flat Plate in Viscous Flow

Go Skin Friction Drag Force = Dynamic Pressure*Reference Area*Skin friction coefficient

Adiabatic Wall Enthalpy using Recovery Factor

Go Adiabatic Wall Enthalpy = Static Enthalpy+Recovery Factor*(Static Velocity^2)/2

Coefficient of Friction using Stanton Number for Flat Plate Case

Go Coefficient of Friction = (2*Stanton Number)/(Prandtl Number^(-2/3))

Stanton Number with Coefficient of Friction

Go Stanton Number = 0.5*Coefficient of Friction*Prandtl Number^(-2/3)

Total Enthalpy in Inviscid Flow Outside Boundary Layer

Go Total Specific Enthalpy = Static Enthalpy+(Static Velocity^2)/2

Recovery Factor Calculation using Prandtl Number

Go Recovery Factor = sqrt(Prandtl Number)

Prandtl Number for Flat Plate with Viscous Flow

Go Prandtl Number = Recovery Factor^2

Skin-Friction Drag for Flat Plate in Viscous Flow Formula

Skin Friction Drag Force = Dynamic Pressure*Reference Area*Skin friction coefficient
F_skin = q*S*c_f

What is a skin friction drag?

Friction Drag, also known as Skin Friction Drag, is drag caused by the friction of a fluid against the surface of an object that is moving through it.

How to Calculate Skin-Friction Drag for Flat Plate in Viscous Flow?

Skin-Friction Drag for Flat Plate in Viscous Flow calculator uses Skin Friction Drag Force = Dynamic Pressure*Reference Area*Skin friction coefficient to calculate the Skin Friction Drag Force, The Skin-friction drag for flat plate in viscous flow formula is defined as the product of dynamic pressure, reference area, and skin friction coefficient. Skin Friction Drag Force is denoted by F_skin symbol.

How to calculate Skin-Friction Drag for Flat Plate in Viscous Flow using this online calculator? To use this online calculator for Skin-Friction Drag for Flat Plate in Viscous Flow, enter Dynamic Pressure (q), Reference Area (S) & Skin friction coefficient (c_f) and hit the calculate button. Here is how the Skin-Friction Drag for Flat Plate in Viscous Flow calculation can be explained with given input values -> 36.576 = 10*5.08*0.72.

FAQ

What is Skin-Friction Drag for Flat Plate in Viscous Flow?

The Skin-friction drag for flat plate in viscous flow formula is defined as the product of dynamic pressure, reference area, and skin friction coefficient and is represented as F_skin = q*S*c_f or Skin Friction Drag Force = Dynamic Pressure*Reference Area*Skin friction coefficient. Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Skin friction coefficient is an important dimensionless parameter in boundary-layer flows. It specifies the fraction of the local dynamic pressure.

How to calculate Skin-Friction Drag for Flat Plate in Viscous Flow?

The Skin-friction drag for flat plate in viscous flow formula is defined as the product of dynamic pressure, reference area, and skin friction coefficient is calculated using Skin Friction Drag Force = Dynamic Pressure*Reference Area*Skin friction coefficient. To calculate Skin-Friction Drag for Flat Plate in Viscous Flow, you need Dynamic Pressure (q), Reference Area (S) & Skin friction coefficient (c_f). With our tool, you need to enter the respective value for Dynamic Pressure, Reference Area & Skin friction coefficient 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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