Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Heat Loss due to Pipe
Heat Loss due to Pipe=(Force*Length*Fluid Velocity^2)/(2*Diameter *Acceleration Due To Gravity) GO
Reynolds Number for Circular Tubes
Reynolds Number=Density*Fluid Velocity*Diameter /Dynamic viscosity GO
Perimeter of a Semicircle when circumference of circle is given
Perimeter=(Circumference of Circle/2)+Diameter GO
Diameter of circumscribing sphere when diameter and height of circumscribed cylinder is known
Diameter of Sphere=sqrt(Diameter ^2+Height^2) GO
Cutting Speed
Cutting Speed=pi*Diameter *Angular Speed GO
Area of a Circle when diameter is given
Area of Circle=(pi/4)*Diameter ^2 GO
Perimeter of a quarter circle when diameter is given
Perimeter=Diameter *((pi/4)+1) GO
Perimeter of a Semicircle when diameter is given
Perimeter=Diameter *((pi/2)+1) GO
Area of a quarter circle when diameter is given
Area=(pi*(Diameter )^2)/16 GO
Area of a Semicircle when diameter is given
Area=(pi*(Diameter )^2)/8 GO
Radius of a circle when diameter is given
Radius=Diameter /2 GO

11 Other formulas that calculate the same Output

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag coefficient of flat plate laminar flow given Schmidt number
Drag Coefficient=(2*Convective mass transfer coefficient*(Schmidt Number^0.67))/Free stream velocity GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO
Coefficient of drag equation with coefficient of normal force
Drag Coefficient=coefficient of force*sin(Angle of attack) GO
Coefficient of Drag for given thrust-to-weight ratio
Drag Coefficient=lift coefficient*Thrust-to-weight ratio GO
Coefficient of drag
Drag Coefficient=Drag Force/(Dynamic Pressure*Area) GO
Drag coefficient of flat plate in combined laminar turbulent flow
Drag Coefficient=0.0571/(Reynolds Number^0.2) GO
Drag coefficient of flat plate laminar flow
Drag Coefficient=0.644/(Reynolds Number^0.5) GO
Coefficient of drag equation with angle of attack
Drag Coefficient=2*(sin(Angle of attack))^3 GO
drag coefficient of flat plate laminar flow given friction factor
Drag Coefficient=Friction factor/4 GO

Coefficient of drag equation using energy released from blast wave Formula

Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter )
C<sub>D</sub>=e/(0.5*ρ<sub>∞</sub>*(V<sub>∞</sub>^2)*d)
More formulas
Pressure for the cylindrical blast wave GO
Boltzmann constant for cylindrical blast wave GO
formula For creation pressure for the planar blast wave GO
Radial coordinate of cylindrical blast wave GO
Radial coordinate for the planar blast wave, GO
Energy for the blast wave GO
Time required for the blast wave GO
Modified pressure equation for cylindrical blast wave GO
Pressure ratio for blunt cylinder blast wave GO
Simplified pressure ratio for blunt cylinder blast wave GO
Modified Radial coordinate equation for cylindrical blast wave GO
Modified Energy for the cylindrical blast wave GO
Pressure ratio for blunt slab blast wave GO
Radial coordinate of blunt slab blast wave GO
Blunt-nosed flat plate pressure ratio (first approximation) GO

What is a drag coefficient?

The drag coefficient is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and flow conditions on aircraft drag

How to Calculate Coefficient of drag equation using energy released from blast wave?

Coefficient of drag equation using energy released from blast wave calculator uses Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter ) to calculate the Drag Coefficient, The Coefficient of drag equation using energy released from blast wave formula is defined as the ratio of energy released and half of product of freestream density, square of freestream velocity and base diameter . Drag Coefficient and is denoted by CD symbol.

How to calculate Coefficient of drag equation using energy released from blast wave using this online calculator? To use this online calculator for Coefficient of drag equation using energy released from blast wave, enter Energy (e), Freestream density ), Freestream Velocity (V) and Diameter (d) and hit the calculate button. Here is how the Coefficient of drag equation using energy released from blast wave calculation can be explained with given input values -> 1.633E-5 = 1/(0.5*1.225*(100^2)*10).

FAQ

What is Coefficient of drag equation using energy released from blast wave?
The Coefficient of drag equation using energy released from blast wave formula is defined as the ratio of energy released and half of product of freestream density, square of freestream velocity and base diameter and is represented as CD=e/(0.5*ρ*(V^2)*d) or Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter ). Energy is the amount of work done, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air and Diameter is a straight line passing from side to side through the center of a body or figure, especially a circle or sphere.
How to calculate Coefficient of drag equation using energy released from blast wave?
The Coefficient of drag equation using energy released from blast wave formula is defined as the ratio of energy released and half of product of freestream density, square of freestream velocity and base diameter is calculated using Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter ). To calculate Coefficient of drag equation using energy released from blast wave, you need Energy (e), Freestream density ), Freestream Velocity (V) and Diameter (d). With our tool, you need to enter the respective value for Energy, Freestream density, Freestream Velocity and Diameter 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 Drag Coefficient?
In this formula, Drag Coefficient uses Energy, Freestream density, Freestream Velocity and Diameter . We can use 11 other way(s) to calculate the same, which is/are as follows -
  • Drag Coefficient=Drag Force/(Dynamic Pressure*Area)
  • Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Drag Coefficient=lift coefficient*Thrust-to-weight ratio
  • Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight
  • Drag Coefficient=coefficient of force*sin(Angle of attack)
  • Drag Coefficient=2*(sin(Angle of attack))^3
  • Drag Coefficient=0.644/(Reynolds Number^0.5)
  • Drag Coefficient=(2*Convective mass transfer coefficient*(Schmidt Number^0.67))/Free stream velocity
  • Drag Coefficient=Friction factor/4
  • Drag Coefficient=0.0571/(Reynolds Number^0.2)
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!