Nose radius of cylinder-wedge Calculator

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✖Local shock-detachment distance , is the distance of shock formation from leading edgeⓘ Local shock-detachment distance [𝛿]			+10% -10%
✖Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of soundⓘ Mach Number [M]			+10% -10%

✖Radius is a radial line from the focus to any point of a curve.ⓘ Nose radius of cylinder-wedge [r]

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Nose radius of cylinder-wedge

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

Exact Density Ratio

Density ratio=((Specific Heat Ratio+1)*((Mach Number*(sin(Wave angle)))^2))/((Specific Heat Ratio-1)*((Mach Number*(sin(Wave angle)))^2)+2) GO

Temperature ratio when Mach becomes infinite

Temperature Ratio=(2*Specific Heat Ratio*(Specific Heat Ratio-1))*((Mach Number*sin(Wave angle))^2)/(Specific Heat Ratio+1)^2 GO

Ratio of stagnation and static pressure

Stagnation to Static Pressure=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(Specific Heat Ratio/(Specific Heat Ratio-1)) GO

Ratio of Stagnation and Static Density

Stagnation to Static Density=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(1/(Specific Heat Ratio-1)) GO

Relation between Characteristic Mach number and Mach number

Characteristic Mach number=((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number^2))))^0.5 GO

Exact pressure ratio

pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO

Pressure ratio when Mach becomes infinite

pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2) GO

Exact relation for pressure coefficient behind an oblique shock wave

Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2)) GO

Ratio of Stagnation and Static Temperature

Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO

Dynamic pressure for given specific heat ratio and Mach number

Dynamic Pressure=Specific heat ratio*Static pressure*(Mach Number^2)/2 GO

Mach Angle

Mach Angle=asin(1/Mach Number) GO

< 11 Other formulas that calculate the same Output

Radius of the circumcircle of a triangle

Radius=((Side A)*(Side B)*(Side C))/4*(sqrt(Semiperimeter *(Semiperimeter -Side A)*(Semiperimeter -Side B)*(Semiperimeter -Side C))) GO

Radius Of The Orbit

Radius=(Quantum Number*Plancks Constant)/(2*pi*Mass*Velocity) GO

Bohr's Radius

Radius=(Quantum Number/Atomic number)*0.529*10^-10 GO

Inner radius of a hallow cylinder

Radius=(Inner curved surface area)/(2*pi*Height) GO

Radius of circle when area of sector and angle are given

Radius=(2*Area of Sector/Central Angle)^0.5 GO

Outer radius of hollow cylinder

Radius=(Outer surface area)/(2*pi*Height) GO

Radius of a circle when circumference is given

Radius=(Circumference of Circle)/(pi*2) GO

Radius of a circle when area is given

Radius=sqrt(Area of Circle/pi) GO

Radius of Sphere

Radius=(1/2)*sqrt(Area/pi) GO

Radius of the circumscribed circle of an equilateral triangle if given side

Radius=Side/sqrt(3) GO

Radius of a circle when diameter is given

Radius=Diameter /2 GO

Nose radius of cylinder-wedge Formula

Radius=Local shock-detachment distance/((0.386*exp(4.67/(Mach Number^2))))
r=𝛿/((0.386*exp(4.67/(M^2))))

More formulas

Grid point calculation for shock waves GO

Mach wave behind the shock GO

Mach wave behind the shock with mach infinity GO

Local shock velocity equation GO

Pressure ratio for unsteady waves GO

Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves GO

Temperature ratio for unsteady compression waves GO

Temperature ratio for unsteady expansion wave GO

New pressure after the shock formation for compression wave GO

New pressure after the shock formation, subtracted to velocity for expansion wave GO

Density before shock formation for compression wave GO

Density before the shock formation for expansion wave GO

Ratio of new and old temperature GO

Ratio of new and old temperature for expansion waves GO

Detachment distance of sphere cone GO

Nose radius of sphere cone GO

Detachment distance of cylinder-wedge GO

What is a shock wave?

The shock wave, a strong pressure wave in an elastic medium such as air, water, or a solid substance, produced by supersonic aircraft, explosions, lightning, or other phenomena that create violent changes in pressure.

How to Calculate Nose radius of cylinder-wedge?

Nose radius of cylinder-wedge calculator uses Radius=Local shock-detachment distance/((0.386*exp(4.67/(Mach Number^2)))) to calculate the Radius, The Nose radius of cylinder-wedge formula is defined as the ratio of shock wave detachment distance to the exponent of inverse of the square of mach number at infinity. Radius and is denoted by r symbol.

How to calculate Nose radius of cylinder-wedge using this online calculator? To use this online calculator for Nose radius of cylinder-wedge, enter Local shock-detachment distance (𝛿) and Mach Number (M) and hit the calculate button. Here is how the Nose radius of cylinder-wedge calculation can be explained with given input values -> 0.002428 = 0.001/((0.386*exp(4.67/(1^2)))).

FAQ

What is Nose radius of cylinder-wedge?

The Nose radius of cylinder-wedge formula is defined as the ratio of shock wave detachment distance to the exponent of inverse of the square of mach number at infinity and is represented as r=𝛿/((0.386*exp(4.67/(M^2)))) or Radius=Local shock-detachment distance/((0.386*exp(4.67/(Mach Number^2)))). Local shock-detachment distance , is the distance of shock formation from leading edge and Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.

How to calculate Nose radius of cylinder-wedge?

The Nose radius of cylinder-wedge formula is defined as the ratio of shock wave detachment distance to the exponent of inverse of the square of mach number at infinity is calculated using Radius=Local shock-detachment distance/((0.386*exp(4.67/(Mach Number^2)))). To calculate Nose radius of cylinder-wedge, you need Local shock-detachment distance (𝛿) and Mach Number (M). With our tool, you need to enter the respective value for Local shock-detachment distance and Mach Number 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 Radius?

In this formula, Radius uses Local shock-detachment distance and Mach Number. We can use 11 other way(s) to calculate the same, which is/are as follows -

Radius=(Circumference of Circle)/(pi*2)
Radius=sqrt(Area of Circle/pi)
Radius=Diameter /2
Radius=(Quantum Number/Atomic number)*0.529*10^-10
Radius=(Quantum Number*Plancks Constant)/(2*pi*Mass*Velocity)
Radius=(1/2)*sqrt(Area/pi)
Radius=(2*Area of Sector/Central Angle)^0.5
Radius=(Inner curved surface area)/(2*pi*Height)
Radius=(Outer surface area)/(2*pi*Height)
Radius=((Side A)*(Side B)*(Side C))/4*(sqrt(Semiperimeter *(Semiperimeter -Side A)*(Semiperimeter -Side B)*(Semiperimeter -Side C)))
Radius=Side/sqrt(3)

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