Local Heat Transfer Rate Calculation using Stanton Number Calculator

✖The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.ⓘ Stanton Number [St]			+10% -10%
✖The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.ⓘ Static Density [ρ_e]			+10% -10%
✖The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.ⓘ Static Velocity [u_e]			+10% -10%
✖The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects.ⓘ Adiabatic Wall Enthalpy [h_aw]			+10% -10%
✖The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.ⓘ Wall Enthalpy [h_w]			+10% -10%

✖The Local Heat Transfer Rate is the amount of heat transferred per unit area per unit time from the surface to the fluid in a hypersonic boundary layer.ⓘ Local Heat Transfer Rate Calculation using Stanton Number [q_w]

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Local Heat Transfer Rate Calculation using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Local Heat Transfer Rate = Stanton Number*Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)
q_w = St*ρ_e*u_e*(h_aw-h_w)
This formula uses 6 Variables

Variables Used

Local Heat Transfer Rate - (Measured in Watt per Square Meter) - The Local Heat Transfer Rate is the amount of heat transferred per unit area per unit time from the surface to the fluid in a hypersonic boundary layer.
Stanton Number - The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.
Static Density - (Measured in Kilogram per Cubic Meter) - The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.
Static Velocity - (Measured in Meter per Second) - The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.
Adiabatic Wall Enthalpy - (Measured in Joule per Kilogram) - The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects.
Wall Enthalpy - (Measured in Joule per Kilogram) - The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.

STEP 1: Convert Input(s) to Base Unit

Stanton Number: 0.4 --> 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

q_w = St*ρ_e*u_e*(h_aw-h_w) --> 0.4*1200*8.8*(102-99.2)

Evaluating ... ...

q_w = 11827.2

STEP 3: Convert Result to Output's Unit

11827.2 Watt per Square Meter --> No Conversion Required

FINAL ANSWER

11827.2 Watt per Square Meter <-- Local Heat Transfer Rate

(Calculation completed in 00.004 seconds)

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Amrita School of Engineering (ASE), Vallikavu

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< Local Heat Transfer for Hypersonic Flow Calculators

Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number

LaTeX 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

LaTeX 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

LaTeX Go Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))

Stanton Number for Hypersonic Vehicle

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

Local Heat Transfer Rate Calculation using Stanton Number Formula

LaTeX Go

Local Heat Transfer Rate = Stanton Number*Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)
q_w = St*ρ_e*u_e*(h_aw-h_w)

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 Local Heat Transfer Rate Calculation using Stanton Number?

Local Heat Transfer Rate Calculation using Stanton Number calculator uses Local Heat Transfer Rate = Stanton Number*Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy) to calculate the Local Heat Transfer Rate, Local Heat Transfer Rate Calculation using Stanton Number formula is defined as a method to quantify the heat transfer rate between a surface and a fluid in hypersonic flow, providing a crucial parameter in understanding heat transfer mechanisms in high-speed flows. Local Heat Transfer Rate is denoted by q_w symbol.

How to calculate Local Heat Transfer Rate Calculation using Stanton Number using this online calculator? To use this online calculator for Local Heat Transfer Rate Calculation using Stanton Number, enter Stanton Number (St), Static Density (ρ_e), Static Velocity (u_e), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w) and hit the calculate button. Here is how the Local Heat Transfer Rate Calculation using Stanton Number calculation can be explained with given input values -> 11827.2 = 0.4*1200*8.8*(102-99.2).

FAQ

What is Local Heat Transfer Rate Calculation using Stanton Number?

Local Heat Transfer Rate Calculation using Stanton Number formula is defined as a method to quantify the heat transfer rate between a surface and a fluid in hypersonic flow, providing a crucial parameter in understanding heat transfer mechanisms in high-speed flows and is represented as q_w = St*ρ_e*u_e*(h_aw-h_w) or Local Heat Transfer Rate = Stanton Number*Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy). The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow, The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions, The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface, The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects & The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.

How to calculate Local Heat Transfer Rate Calculation using Stanton Number?

Local Heat Transfer Rate Calculation using Stanton Number formula is defined as a method to quantify the heat transfer rate between a surface and a fluid in hypersonic flow, providing a crucial parameter in understanding heat transfer mechanisms in high-speed flows is calculated using Local Heat Transfer Rate = Stanton Number*Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy). To calculate Local Heat Transfer Rate Calculation using Stanton Number, you need Stanton Number (St), Static Density (ρ_e), Static Velocity (u_e), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w). With our tool, you need to enter the respective value for Stanton Number, 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 Local Heat Transfer Rate?

In this formula, Local Heat Transfer Rate uses Stanton Number, 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 -

Local Heat Transfer Rate = (Nusselt Number*Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))/(Distance from Nose Tip to Required Base Diameter)

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