Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow Calculator

✖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 [C_f]			+10% -10%
✖The Prandtl number (Pr) or Prandtl group is a dimensionless number, named after the German physicist Ludwig Prandtl, defined as the ratio of momentum diffusivity to thermal diffusivity.ⓘ Prandtl Number [Pr]			+10% -10%

✖The Stanton number is a dimensionless number that measures the ratio of heat transferred into a fluid to the thermal capacity of the fluid.ⓘ Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow [St]

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Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow

Formula

`"St" = "C"_{"f"}*0.5*"Pr"^(-2/3)`

Example

`"0.424925"="0.67"*0.5*("0.7")^(-2/3)`

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Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow Solution

STEP 0: Pre-Calculation Summary

Formula Used

Stanton Number = Overall Skin-friction Drag Coefficient*0.5*Prandtl Number^(-2/3)
St = C_f*0.5*Pr^(-2/3)
This formula uses 3 Variables

Variables Used

Stanton Number - The Stanton number is a dimensionless number that measures the ratio of heat transferred into a fluid to the thermal capacity of the fluid.
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.
Prandtl Number - The Prandtl number (Pr) or Prandtl group is a dimensionless number, named after the German physicist Ludwig Prandtl, defined as the ratio of momentum diffusivity to thermal diffusivity.

STEP 1: Convert Input(s) to Base Unit

Overall Skin-friction Drag Coefficient: 0.67 --> No Conversion Required
Prandtl Number: 0.7 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

St = C_f*0.5*Pr^(-2/3) --> 0.67*0.5*0.7^(-2/3)

Evaluating ... ...

St = 0.424925486548245

STEP 3: Convert Result to Output's Unit

0.424925486548245 --> No Conversion Required

FINAL ANSWER

0.424925486548245 ≈ 0.424925 <-- Stanton Number

(Calculation completed in 00.004 seconds)

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Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Viscous Flow Fundamentals » Aero-Thermal Dynamics » Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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Indian Institute of Technology (IIT), Bombay

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< 16 Aero-Thermal Dynamics Calculators

Aerodynamic Heating to Surface

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

Static Viscosity Calculation using Chapman-Rubesin Factor

Go Static Viscosity = (Density*Kinematic Viscosity)/(Chapman–Rubesin factor*Static Density)

Static Density Calculation using Chapman-Rubesin Factor

Go Static Density = (Density*Kinematic Viscosity)/(Chapman–Rubesin factor*Static Viscosity)

Chapman-Rubesin Factor

Go Chapman–Rubesin factor = (Density*Kinematic Viscosity)/(Static Density*Static Viscosity)

Viscosity Calculation using Chapman-Rubesin Factor

Go Kinematic Viscosity = Chapman–Rubesin factor*Static Density*Static Viscosity/(Density)

Density Calculation using Chapman-Rubesin Factor

Go Density = Chapman–Rubesin factor*Static Density*Static Viscosity/(Kinematic Viscosity)

Thermal Conductivity using Prandtl Number

Go Thermal Conductivity = (Dynamic Viscosity*Specific Heat Capacity at Constant Pressure)/Prandtl Number

Non Dimensional Internal Energy Parameter

Go Non-Dimensional Internal Energy = Internal Energy/(Specific Heat Capacity*Temperature)

Stanton Number for Incompressible Flow

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

Wall Temperature Calculation using Internal Energy Change

Go Temperature of wall in Kelvin = Non-Dimensional Internal Energy*Free Stream Temperature

Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow

Go Stanton Number = Overall Skin-friction Drag Coefficient*0.5*Prandtl Number^(-2/3)

Non Dimensional Internal Energy Parameter using Wall-to-Freestream Temperature Ratio

Go Non-Dimensional Internal Energy = Wall Temperature/Free Stream Temperature

Internal Energy for Hypersonic Flow

Go Internal Energy = Enthalpy+Pressure/Density

Non Dimensional Static Enthalpy

Go Non Dimensional Static Enthalpy = Stagnation Enthalpy/Static Enthalpy

Coefficient of Friction using Stanton Equation for Incompressible Flow

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

Static Enthalpy

Go Static Enthalpy = Enthalpy/Non Dimensional Static Enthalpy

Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow Formula

Stanton Number = Overall Skin-friction Drag Coefficient*0.5*Prandtl Number^(-2/3)
St = C_f*0.5*Pr^(-2/3)

What is Stanton number?

The Stanton number, St, is a dimensionless number that measures the ratio of heat transferred into a fluid to the thermal capacity of fluid

How to Calculate Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow?

Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow calculator uses Stanton Number = Overall Skin-friction Drag Coefficient*0.5*Prandtl Number^(-2/3) to calculate the Stanton Number, Stanton equation using Overall skin friction coefficient for incompressible flow formula is defined as the product of coefficient of friction to the Prandtl number raise power of -2/3. Stanton Number is denoted by St symbol.

How to calculate Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow using this online calculator? To use this online calculator for Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow, enter Overall Skin-friction Drag Coefficient (C_f) & Prandtl Number (Pr) and hit the calculate button. Here is how the Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow calculation can be explained with given input values -> 0.424925 = 0.67*0.5*0.7^(-2/3).

FAQ

What is Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow?

Stanton equation using Overall skin friction coefficient for incompressible flow formula is defined as the product of coefficient of friction to the Prandtl number raise power of -2/3 and is represented as St = C_f*0.5*Pr^(-2/3) or Stanton Number = Overall Skin-friction Drag Coefficient*0.5*Prandtl Number^(-2/3). Overall Skin-friction Drag Coefficient is an important dimensionless parameter in boundary-layer flows. It specifies the fraction of the local dynamic pressure & The Prandtl number (Pr) or Prandtl group is a dimensionless number, named after the German physicist Ludwig Prandtl, defined as the ratio of momentum diffusivity to thermal diffusivity.

How to calculate Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow?

Stanton equation using Overall skin friction coefficient for incompressible flow formula is defined as the product of coefficient of friction to the Prandtl number raise power of -2/3 is calculated using Stanton Number = Overall Skin-friction Drag Coefficient*0.5*Prandtl Number^(-2/3). To calculate Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow, you need Overall Skin-friction Drag Coefficient (C_f) & Prandtl Number (Pr). With our tool, you need to enter the respective value for Overall Skin-friction Drag Coefficient & Prandtl Number 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 Stanton Number?

In this formula, Stanton Number uses Overall Skin-friction Drag Coefficient & Prandtl Number. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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