- 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:[87]where
- L is lift force,
- ρ is air density
- v is true airspeed,
- A is planform area, and
is the lift coefficient at the desired angle of attack, Mach number, and Reynolds number[88]
Saturday, November 3, 2012
Lift coefficient
Subscribe to:
Post Comments (Atom)
No comments:
Post a Comment