Lift coefficient
Main article: Lift coefficient
If the lift coefficient for a wing at a specified angle of attack is known (or estimated using a method such as thin-airfoil theory), then the lift produced for specific flow conditions can be determined using the following equation:[46]
Main article: Lift coefficient
If the lift coefficient for a wing at a specified angle of attack is known (or estimated using a method such as thin-airfoil theory), then the lift produced for specific flow conditions can be determined using the following equation:[46]
where
L is lift force,
ρ is air density
v is true airspeed,
A is planform area, and
CL is the lift coefficient at the desired angle of attack, Mach number, and Reynolds number[47]
This equation is basically the same as the drag equation, only the lift/drag coefficient is different.
L is lift force,
ρ is air density
v is true airspeed,
A is planform area, and
CL is the lift coefficient at the desired angle of attack, Mach number, and Reynolds number[47]
This equation is basically the same as the drag equation, only the lift/drag coefficient is different.
No comments:
Post a Comment