Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 200+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

10 Other formulas that you can solve using the same Inputs

Pressure coefficient combined with blast wave for the shuttle at angle of attack
Pressure coefficient=(0.0137/(Distance from X-axis/Length of the shuttle))+2*(sin(Angle of attack))^2 GO
Velocity of airfoil for circulation developed on the airfoil
velocity of airfoil=Circulation/(pi*Chord Length*sin(Angle of attack)) GO
Chord length for circulation developed on the airfoil
Chord Length=Circulation/(pi*velocity of airfoil*sin(Angle of attack)) GO
Circulation developed on the airfoil
Circulation=pi*velocity of airfoil*Chord Length*sin(Angle of attack) GO
Coefficient of lift equation with angle of attack
lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack) GO
Coefficient of lift equation with coefficient of normal force
lift coefficient=coefficient of force*cos(Angle of attack) GO
Lift coefficient for symmetrical airfoil by Thin airfoil theory
Lift coefficient for 2D body=2*pi*Angle of attack GO
Coefficient of drag equation with angle of attack
Drag Coefficient=2*(sin(Angle of attack))^3 GO
Lift force with angle of attack
Lift force=Drag Force*cot(Angle of attack) GO
Drag force with angle of attack
Drag Force=Lift force/cot(Angle of attack) 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 equation using energy released from blast wave
Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter ) GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight 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 with coefficient of normal force Formula

Drag Coefficient=coefficient of force*sin(Angle of attack)
C<sub>D</sub>=CN*sin(α)
More formulas
Mass flux incident on a surface area GO
Time rate of change of momentum of the mass flux GO
Force F exerted on the surface GO
Coefficient of lift equation with coefficient of normal force GO
Coefficient of lift equation with angle of attack GO
Coefficient of drag equation with angle of attack GO
Lift force with angle of attack GO
Drag force with angle of attack GO
Modified Newtonian Law GO
Maximum Pressure coefficient GO
exact normal shock-wave maximum coefficient of pressure GO
Pressure coefficient for slender 2-D bodies GO
Pressure coefficient for slender bodies of revolution GO

What is angle of attack?

n fluid dynamics, angle of attack is the angle between a reference line on a body (often the chord line of an airfoil) and the vector representing the relative motion between the body and the fluid through which it is moving.

How to Calculate Coefficient of drag equation with coefficient of normal force?

Coefficient of drag equation with coefficient of normal force calculator uses Drag Coefficient=coefficient of force*sin(Angle of attack) to calculate the Drag Coefficient, The Coefficient of drag equation with coefficient of normal force formula is defined as the product of coefficient of normal force acting on the body and sin of angle of attack. Drag Coefficient and is denoted by CD symbol.

How to calculate Coefficient of drag equation with coefficient of normal force using this online calculator? To use this online calculator for Coefficient of drag equation with coefficient of normal force, enter coefficient of force (CN) and Angle of attack (α) and hit the calculate button. Here is how the Coefficient of drag equation with coefficient of normal force calculation can be explained with given input values -> 0.173648 = 1*sin(10).

FAQ

What is Coefficient of drag equation with coefficient of normal force?
The Coefficient of drag equation with coefficient of normal force formula is defined as the product of coefficient of normal force acting on the body and sin of angle of attack and is represented as CD=CN*sin(α) or Drag Coefficient=coefficient of force*sin(Angle of attack). coefficient of force is the force acting on the reference area with dynamic pressure in case of hypersonic flow and Angle of attack is the angle between a reference line on a body and the vector representing the relative motion between the body and the fluid through which it is moving. .
How to calculate Coefficient of drag equation with coefficient of normal force?
The Coefficient of drag equation with coefficient of normal force formula is defined as the product of coefficient of normal force acting on the body and sin of angle of attack is calculated using Drag Coefficient=coefficient of force*sin(Angle of attack). To calculate Coefficient of drag equation with coefficient of normal force, you need coefficient of force (CN) and Angle of attack (α). With our tool, you need to enter the respective value for coefficient of force and Angle of attack 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 coefficient of force and Angle of attack. 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=2*(sin(Angle of attack))^3
  • Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter )
  • 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!