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

✖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 [q_w]			+10% -10%
✖The Distance from Nose Tip to Required Base Diameter is the length from the nose tip to the base diameter of a hypersonic vehicle's boundary layer.ⓘ Distance from Nose Tip to Required Base Diameter [x_d]			+10% -10%
✖The Nusselt Number is a dimensionless quantity that characterizes the convective heat transfer between a surface and a fluid in hypersonic flow conditions.ⓘ Nusselt Number [N_u]			+10% -10%
✖The Adiabatic Wall Temperature is the temperature at the surface of an object in hypersonic flow, where the heat transfer is zero and the flow is in equilibrium.ⓘ Adiabatic Wall Temperature [T_wall]			+10% -10%
✖The Wall Temperature is the temperature at the surface of the wall in a hypersonic flow, which affects the flow's thermal and velocity boundary layers.ⓘ Wall Temperature [Tw]			+10% -10%

✖The Thermal Conductivity is a measure of the ability of a material to conduct heat in the hypersonic boundary layer, characterizing heat transfer properties.ⓘ Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number [k]

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

STEP 0: Pre-Calculation Summary

Formula Used

Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature))
k = (q_w*x_d)/(N_u*(T_wall-Tw))
This formula uses 6 Variables

Variables Used

Thermal Conductivity - (Measured in Watt per Meter per K) - The Thermal Conductivity is a measure of the ability of a material to conduct heat in the hypersonic boundary layer, characterizing heat transfer properties.
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.
Distance from Nose Tip to Required Base Diameter - (Measured in Meter) - The Distance from Nose Tip to Required Base Diameter is the length from the nose tip to the base diameter of a hypersonic vehicle's boundary layer.
Nusselt Number - The Nusselt Number is a dimensionless quantity that characterizes the convective heat transfer between a surface and a fluid in hypersonic flow conditions.
Adiabatic Wall Temperature - (Measured in Kelvin) - The Adiabatic Wall Temperature is the temperature at the surface of an object in hypersonic flow, where the heat transfer is zero and the flow is in equilibrium.
Wall Temperature - (Measured in Kelvin) - The Wall Temperature is the temperature at the surface of the wall in a hypersonic flow, which affects the flow's thermal and velocity boundary layers.

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
Distance from Nose Tip to Required Base Diameter: 1.2 Meter --> 1.2 Meter No Conversion Required
Nusselt Number: 1400 --> No Conversion Required
Adiabatic Wall Temperature: 125 Kelvin --> 125 Kelvin No Conversion Required
Wall Temperature: 15 Kelvin --> 15 Kelvin No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

k = (q_w*x_d)/(N_u*(T_wall-Tw)) --> (12000*1.2)/(1400*(125-15))

Evaluating ... ...

k = 0.0935064935064935

STEP 3: Convert Result to Output's Unit

0.0935064935064935 Watt per Meter per K --> No Conversion Required

FINAL ANSWER

0.0935064935064935 ≈ 0.093506 Watt per Meter per K <-- Thermal Conductivity

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

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))

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

LaTeX Go

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

What is Nusselt's number?

The Nusselt number is the ratio of convective to conductive heat transfer across a boundary. The convection and conduction heat flows are parallel to each other and to the surface normal of the boundary surface, and are all perpendicular to the mean fluid flow in the simple case.

How to Calculate Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number?

Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number calculator uses Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature)) to calculate the Thermal Conductivity, Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number formula is defined as a measure of the ability of a material to conduct heat at the edge of the boundary layer in hypersonic flow, which is crucial in understanding heat transfer and fluid dynamics in high-speed flows. Thermal Conductivity is denoted by k symbol.

How to calculate Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number using this online calculator? To use this online calculator for Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number, enter Local Heat Transfer Rate (q_w), Distance from Nose Tip to Required Base Diameter (x_d), Nusselt Number (N_u), Adiabatic Wall Temperature (T_wall) & Wall Temperature (Tw) and hit the calculate button. Here is how the Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number calculation can be explained with given input values -> 0.093506 = (12000*1.2)/(1400*(125-15)).

FAQ

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

Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number formula is defined as a measure of the ability of a material to conduct heat at the edge of the boundary layer in hypersonic flow, which is crucial in understanding heat transfer and fluid dynamics in high-speed flows and is represented as k = (q_w*x_d)/(N_u*(T_wall-Tw)) or Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature)). 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, The Distance from Nose Tip to Required Base Diameter is the length from the nose tip to the base diameter of a hypersonic vehicle's boundary layer, The Nusselt Number is a dimensionless quantity that characterizes the convective heat transfer between a surface and a fluid in hypersonic flow conditions, The Adiabatic Wall Temperature is the temperature at the surface of an object in hypersonic flow, where the heat transfer is zero and the flow is in equilibrium & The Wall Temperature is the temperature at the surface of the wall in a hypersonic flow, which affects the flow's thermal and velocity boundary layers.

How to calculate Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number?

Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number formula is defined as a measure of the ability of a material to conduct heat at the edge of the boundary layer in hypersonic flow, which is crucial in understanding heat transfer and fluid dynamics in high-speed flows is calculated using Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature)). To calculate Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number, you need Local Heat Transfer Rate (q_w), Distance from Nose Tip to Required Base Diameter (x_d), Nusselt Number (N_u), Adiabatic Wall Temperature (T_wall) & Wall Temperature (Tw). With our tool, you need to enter the respective value for Local Heat Transfer Rate, Distance from Nose Tip to Required Base Diameter, Nusselt Number, Adiabatic Wall Temperature & Wall Temperature 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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