Stanton Number for Hypersonic Vehicle 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: 1200 Kilogram per Cubic Meter --> 1200 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/(1200*8.8*(102-99.2))
Evaluating ... ...
St = 0.405844155844156
STEP 3: Convert Result to Output's Unit
0.405844155844156 --> No Conversion Required
FINAL ANSWER
0.405844155844156 0.405844 <-- Stanton Number
(Calculation completed in 00.004 seconds)

Credits

Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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PSG College of Technology (PSGCT), Coimbatore
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9 Local Heat Transfer for Hypersonic Flow Calculators

Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number
Go Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature))
Local Heat Transfer Rate using Nusselt's Number
Go Local Heat Transfer Rate = (Nusselt Number*Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))/(Distance from Nose Tip to Required Base Diameter)
Nusselt Number for Hypersonic Vehicle
Go Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))
Static Density Equation using Stanton Number
Go Static Density = Local Heat Transfer Rate/(Stanton Number*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Stanton Number for Hypersonic Vehicle
Go Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Static Velocity using Stanton Number
Go Static Velocity = Local Heat Transfer Rate/(Stanton Number*Static Density*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Local Heat Transfer Rate Calculation using Stanton Number
Go Local Heat Transfer Rate = Stanton Number*Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)
Adiabatic Wall Enthalpy using Stanton Number
Go Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)+Wall Enthalpy
Enthalpy of Wall using Stanton Number
Go Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)

Stanton Number for Hypersonic Vehicle 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 Stanton Number for Hypersonic Vehicle?

Stanton Number for Hypersonic Vehicle calculator uses Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)) to calculate the Stanton Number, Stanton Number for Hypersonic Vehicle is defined as the interrelation as local heat transfer, static density, and velocity of the fluid, adiabatic and wall enthalpy. Stanton Number is denoted by St symbol.

How to calculate Stanton Number for Hypersonic Vehicle using this online calculator? To use this online calculator for Stanton Number for Hypersonic Vehicle, 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 Stanton Number for Hypersonic Vehicle calculation can be explained with given input values -> 0.405844 = 12000/(1200*8.8*(102-99.2)).

FAQ

What is Stanton Number for Hypersonic Vehicle?
Stanton Number for Hypersonic Vehicle is defined as the interrelation as local heat transfer, static density, and velocity of the fluid, adiabatic and wall enthalpy 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 Stanton Number for Hypersonic Vehicle?
Stanton Number for Hypersonic Vehicle is defined as the interrelation as local heat transfer, static density, and velocity of the fluid, adiabatic and wall enthalpy is calculated using Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). To calculate Stanton Number for Hypersonic Vehicle, 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.
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