Aerodynamic Heating Equation for Stanton number Solution

STEP 0: Pre-Calculation Summary
Formula Used
Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
St = qw/(ρe*ue*(haw-hw))
This formula uses 6 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.
Local Heat Transfer Rate - (Measured in Watt per Square Meter) - Local Heat Transfer Rate, is that energy per second per unit area.
Static Density - (Measured in Kilogram per Cubic Meter) - Static density, is the density of the fluid when its not moving, or the density of fluid if we are moving relative to the fluid.
Static Velocity - (Measured in Meter per Second) - Static velocity is the velocity of fluid at a point in the fluid, or velocity in the continuous flow.
Adiabatic Wall Enthalpy - (Measured in Joule per Kilogram) - Adiabatic wall enthalpy, is the Enthalpy of a fluid flowing around a solid body; it corresponds to the adiabatic wall temperature.
Wall Enthalpy - (Measured in Joule per Kilogram) - Wall Enthalpy is the Enthalpy of a fluid flowing around a solid body; it corresponds to the adiabatic wall temperature.
STEP 1: Convert Input(s) to Base Unit
Local Heat Transfer Rate: 12000 Watt per Square Meter --> 12000 Watt per Square Meter No Conversion Required
Static Density: 98.3 Kilogram per Cubic Meter --> 98.3 Kilogram per Cubic Meter No Conversion Required
Static Velocity: 8.8 Meter per Second --> 8.8 Meter per Second No Conversion Required
Adiabatic Wall Enthalpy: 102 Joule per Kilogram --> 102 Joule per Kilogram No Conversion Required
Wall Enthalpy: 99.2 Joule per Kilogram --> 99.2 Joule per Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
St = qw/(ρe*ue*(haw-hw)) --> 12000/(98.3*8.8*(102-99.2))
Evaluating ... ...
St = 4.95435388619519
STEP 3: Convert Result to Output's Unit
4.95435388619519 --> No Conversion Required
FINAL ANSWER
4.95435388619519 4.954354 <-- Stanton Number
(Calculation completed in 00.020 seconds)

Credits

Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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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

Aerodynamic Heating Equation for Stanton number Formula

Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
St = qw/(ρe*ue*(haw-hw))

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 the fluid.

How to Calculate Aerodynamic Heating Equation for Stanton number?

Aerodynamic Heating Equation for Stanton number calculator uses Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)) to calculate the Stanton Number, The Aerodynamic Heating Equation for Stanton number formula is defined as the interrelation between static density, the static velocity of the fluid, Stanton number, and the wall enthalpies. Stanton Number is denoted by St symbol.

How to calculate Aerodynamic Heating Equation for Stanton number using this online calculator? To use this online calculator for Aerodynamic Heating Equation for Stanton number, enter Local Heat Transfer Rate (qw), Static Density e), Static Velocity (ue), Adiabatic Wall Enthalpy (haw) & Wall Enthalpy (hw) and hit the calculate button. Here is how the Aerodynamic Heating Equation for Stanton number calculation can be explained with given input values -> 0.171898 = 12000/(98.3*8.8*(102-99.2)).

FAQ

What is Aerodynamic Heating Equation for Stanton number?
The Aerodynamic Heating Equation for Stanton number formula is defined as the interrelation between static density, the static velocity of the fluid, Stanton number, and the wall enthalpies and is represented as St = qw/(ρe*ue*(haw-hw)) or Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). Local Heat Transfer Rate, is that energy per second per unit area, Static density, is the density of the fluid when its not moving, or the density of fluid if we are moving relative to the fluid, Static velocity is the velocity of fluid at a point in the fluid, or velocity in the continuous flow, Adiabatic wall enthalpy, is the Enthalpy of a fluid flowing around a solid body; it corresponds to the adiabatic wall temperature & Wall Enthalpy is the Enthalpy of a fluid flowing around a solid body; it corresponds to the adiabatic wall temperature.
How to calculate Aerodynamic Heating Equation for Stanton number?
The Aerodynamic Heating Equation for Stanton number formula is defined as the interrelation between static density, the static velocity of the fluid, Stanton number, and the wall enthalpies is calculated using Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). To calculate Aerodynamic Heating Equation for Stanton number, you need Local Heat Transfer Rate (qw), Static Density e), Static Velocity (ue), Adiabatic Wall Enthalpy (haw) & Wall Enthalpy (hw). With our tool, you need to enter the respective value for Local Heat Transfer Rate, Static Density, Static Velocity, Adiabatic Wall Enthalpy & Wall Enthalpy 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 Local Heat Transfer Rate, Static Density, Static Velocity, Adiabatic Wall Enthalpy & Wall Enthalpy. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Stanton Number = 0.5*Coefficient of Friction*Prandtl Number^(-2/3)
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