Thermal conductivity at the edge of the boundary layer equation using Nusselt's number Calculator

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Engineering	Mechanical ↺
Mechanical	Fluid Mechanics ↺
Fluid-Mechanics	Hypersonic Flow ↺
Hypersonic-Flow	Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions ↺

✖Local heat transfer rate, is that energy per second per unit areaⓘ Local heat transfer rate [q_w]			+10% -10%
✖Distance from the nose tip to required base dia, used for studying the leading edge of the hypersonic vehiclesⓘ Distance from the nose tip to required base dia [x]			+10% -10%
✖The Nusselt number is the ratio of convective to conductive heat transfer at a boundary in a fluid. Convection includes both advection and diffusion. The conductive component is measured under the same conditions as the convective but for a hypothetically motionless fluid.ⓘ Nusselt Number [Nu_D]			+10% -10%
✖Adiabatic wall temperature, is the temperature acquired by a wall in liquid or gas flow if the condition of thermal insulation is observed on itⓘ Adiabatic wall temperature [Taw]			+10% -10%
✖Wall temperature is the temperature at the wall.ⓘ Wall temperature [Tw]			+10% -10%

✖Thermal Conductivity is the rate at which heat passes through a specified material, expressed as the amount of heat that flows per unit time through a unit area with a temperature gradient of one degree per unit distance.ⓘ Thermal conductivity at the edge of the boundary layer equation using Nusselt's number [k]

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Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 200+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Nusselt number for hypersonic vehicle

Nusselt Number=((Local heat transfer rate*Distance from the nose tip to required base dia))/(Thermal Conductivity*(Adiabatic wall temperature-Wall temperature)) GO

local heat-transfer rate using Nusselt's number

Local heat transfer rate=(Nusselt Number*Thermal Conductivity*(Adiabatic wall temperature-Wall temperature))/(Distance from the nose tip to required base dia) GO

Static density equation using Stanton number

Static density=Local heat transfer rate/(Stanton Number*Static velocity*(Adiabatic wall enthalpy-Wall enthalpy)) GO

Stanton number for hypersonic vehicle

Stanton Number=Local heat transfer rate/(Static density*Static velocity*(Adiabatic wall enthalpy-Wall enthalpy)) GO

Enthalpy of wall using Stanton number

Wall enthalpy=Adiabatic wall enthalpy-(Local heat transfer rate/(Static density*Static velocity*Stanton Number)) GO

Static velocity using Stanton number

Static velocity=Local heat transfer rate/(Stanton Number*Static density*(Adiabatic wall enthalpy-Wall enthalpy)) GO

Pressure coefficient for Blunt-nosed cylinder:

Pressure coefficient=0.096*(Drag Coefficient^(1/2))/(Distance from the nose tip to required base dia/Diameter ) GO

Adiabatic wall enthalpy using Stanton number

Adiabatic wall enthalpy=Local heat transfer rate/(Static density*Static velocity*Stanton Number)+Wall enthalpy GO

Pressure coefficient combined with blast wave for the shuttle

Pressure coefficient=0.0137/(Distance from the nose tip to required base dia/Length of the shuttle) GO

Non dimensional internal energy parameter using wall-to-freestream temperature ratio

Non dimensional internal energy=Wall temperature/Free stream temperature GO

Stanton Number (using dimensionless numbers)

Stanton Number=Nusselt Number/(Reynolds Number*Prandtl number) GO

< 8 Other formulas that calculate the same Output

Thermal conductivity for a pipe with eccentric lagging

Thermal Conductivity=(heat flow rate*(ln((sqrt(((radius2+radius1)^2)-distance between centres of eccentric circles^2)+sqrt(((radius2-radius1)^2)-distance between centres of eccentric circles^2))/(sqrt(((radius2+radius1)^2)-distance between centres of eccentric circles^2)-sqrt(((radius2-radius1)^2)-distance between centres of eccentric circles^2)))))/(2*pi*Length*(inner surface temperature -outer surface temperature)) GO

Thermal conductivity of base metal using given cooling rate (thin plates)

Thermal Conductivity=Cooling rate/(2*pi*Density*Specific Heat Capacity*((Thickness of the base metal/Net heat supplied per unit length)^2)*((Temperature to calculate cooling rate-Ambient Temperature)^3)) GO

Thermal conductivity of work from tool temperature

Thermal Conductivity=((Constant for tool temperature*Specific cutting energy per unit cutting force*Cutting Velocity^0.44*Area of cut^0.22)/(Tool temperature*Specific Heat Capacity^0.56))^(100/44) GO

Thermal conductivity of a cylindrical wall for a given temperature difference

Thermal Conductivity=((heat flow rate*(ln(radius2/radius1)))/(2*pi*length of cylinder*(inner surface temperature -outer surface temperature))) GO

Thermal conductivity of base metal using given cooling rate (thick plates)

Thermal Conductivity=(Cooling rate*Net heat supplied per unit length)/(2*pi*((Temperature to calculate cooling rate-Ambient Temperature)^2)) GO

Thermal conductivity of the material required to maintain a given temperature difference

Thermal Conductivity=(heat flow rate*Length)/((inner surface temperature -outer surface temperature)*Area) GO

Thermal conductivity using Prandtl number

Thermal Conductivity=(Dynamic viscosity*Specific Heat Capacity at Constant Pressure)/Prandtl number GO

Thermal Conductivity when Critical Thickness of Insulation for a Cylinder is Given

Thermal Conductivity=Critical Thickness of Insulation*Heat transfer coefficient GO

Thermal conductivity at the edge of the boundary layer equation using Nusselt's number Formula

Thermal Conductivity=(Local heat transfer rate*Distance from the nose tip to required base dia)/(Nusselt Number*(Adiabatic wall temperature-Wall temperature))
k=(q<sub>w</sub>*x)/(Nu<sub>D</sub>*(Taw-Tw))

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Local skin-friction coefficient GO

local shear stress at the wall GO

Static Density equation using skin friction coefficient GO

Static velocity equation using skin friction coefficient GO

Nusselt number for hypersonic vehicle GO

local heat-transfer rate using Nusselt's number GO

Stanton number for hypersonic vehicle GO

Local heat-transfer rate calculation using Stanton number GO

Static density equation using Stanton number GO

Static velocity using Stanton number GO

Adiabatic wall enthalpy using Stanton number GO

Enthalpy of wall using Stanton number GO

Nusselt's number with Reynolds number, the Stanton number and Prandtl number GO

Reynolds number for given Nusselt's number, Stanton number and Prandtl number GO

Stanton number with Reynolds number, Nusselt's number, Stanton number and Prandtl number GO

Prandtl number with Reynolds number, Nusselt's number, Stanton number and Stanton number GO

Skin friction coefficient for incompressible flow GO

viscosity around the wall GO

Static viscosity relation using temperature of wall GO

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 the edge of the boundary layer equation using Nusselt's number?

Thermal conductivity at the edge of the boundary layer equation using Nusselt's number calculator uses Thermal Conductivity=(Local heat transfer rate*Distance from the nose tip to required base dia)/(Nusselt Number*(Adiabatic wall temperature-Wall temperature)) to calculate the Thermal Conductivity, The Thermal conductivity at the edge of the boundary layer equation using Nusselt's number formula is defined as the ratio of the product of local heat-transfer rate and distance along the wall measured from the leading edge to the product of Nusselt's number and difference of adiabatic wall temperature and wall temperature. Thermal Conductivity and is denoted by k symbol.

How to calculate Thermal conductivity at the edge of the boundary layer equation using Nusselt's number using this online calculator? To use this online calculator for Thermal conductivity at the edge of the boundary layer equation using Nusselt's number, enter Local heat transfer rate (q_w), Distance from the nose tip to required base dia (x), Nusselt Number (Nu_D), Adiabatic wall temperature (Taw) and Wall temperature (Tw) and hit the calculate button. Here is how the Thermal conductivity at the edge of the boundary layer equation using Nusselt's number calculation can be explained with given input values -> 0.19978 = (10*10)/(5*(100-(-0.11023332720926))).

FAQ

What is Thermal conductivity at the edge of the boundary layer equation using Nusselt's number?

The Thermal conductivity at the edge of the boundary layer equation using Nusselt's number formula is defined as the ratio of the product of local heat-transfer rate and distance along the wall measured from the leading edge to the product of Nusselt's number and difference of adiabatic wall temperature and wall temperature and is represented as k=(q_w*x)/(Nu_D*(Taw-Tw)) or Thermal Conductivity=(Local heat transfer rate*Distance from the nose tip to required base dia)/(Nusselt Number*(Adiabatic wall temperature-Wall temperature)). Local heat transfer rate, is that energy per second per unit area, Distance from the nose tip to required base dia, used for studying the leading edge of the hypersonic vehicles, The Nusselt number is the ratio of convective to conductive heat transfer at a boundary in a fluid. Convection includes both advection and diffusion. The conductive component is measured under the same conditions as the convective but for a hypothetically motionless fluid, Adiabatic wall temperature, is the temperature acquired by a wall in liquid or gas flow if the condition of thermal insulation is observed on it and Wall temperature is the temperature at the wall.

How to calculate Thermal conductivity at the edge of the boundary layer equation using Nusselt's number?

The Thermal conductivity at the edge of the boundary layer equation using Nusselt's number formula is defined as the ratio of the product of local heat-transfer rate and distance along the wall measured from the leading edge to the product of Nusselt's number and difference of adiabatic wall temperature and wall temperature is calculated using Thermal Conductivity=(Local heat transfer rate*Distance from the nose tip to required base dia)/(Nusselt Number*(Adiabatic wall temperature-Wall temperature)). To calculate Thermal conductivity at the edge of the boundary layer equation using Nusselt's number, you need Local heat transfer rate (q_w), Distance from the nose tip to required base dia (x), Nusselt Number (Nu_D), Adiabatic wall temperature (Taw) and Wall temperature (Tw). With our tool, you need to enter the respective value for Local heat transfer rate, Distance from the nose tip to required base dia, Nusselt Number, Adiabatic wall temperature and Wall temperature 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 Thermal Conductivity?

In this formula, Thermal Conductivity uses Local heat transfer rate, Distance from the nose tip to required base dia, Nusselt Number, Adiabatic wall temperature and Wall temperature. We can use 8 other way(s) to calculate the same, which is/are as follows -

Thermal Conductivity=Critical Thickness of Insulation*Heat transfer coefficient
Thermal Conductivity=(heat flow rate*Length)/((inner surface temperature -outer surface temperature)*Area)
Thermal Conductivity=((heat flow rate*(ln(radius2/radius1)))/(2*pi*length of cylinder*(inner surface temperature -outer surface temperature)))
Thermal Conductivity=(Dynamic viscosity*Specific Heat Capacity at Constant Pressure)/Prandtl number
Thermal Conductivity=(Cooling rate*Net heat supplied per unit length)/(2*pi*((Temperature to calculate cooling rate-Ambient Temperature)^2))
Thermal Conductivity=Cooling rate/(2*pi*Density*Specific Heat Capacity*((Thickness of the base metal/Net heat supplied per unit length)^2)*((Temperature to calculate cooling rate-Ambient Temperature)^3))
Thermal Conductivity=(heat flow rate*(ln((sqrt(((radius2+radius1)^2)-distance between centres of eccentric circles^2)+sqrt(((radius2-radius1)^2)-distance between centres of eccentric circles^2))/(sqrt(((radius2+radius1)^2)-distance between centres of eccentric circles^2)-sqrt(((radius2-radius1)^2)-distance between centres of eccentric circles^2)))))/(2*pi*Length*(inner surface temperature -outer surface temperature))
Thermal Conductivity=((Constant for tool temperature*Specific cutting energy per unit cutting force*Cutting Velocity^0.44*Area of cut^0.22)/(Tool temperature*Specific Heat Capacity^0.56))^(100/44)

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