For cylinders coefficient of lift is approximately half of coefficient of drag while they are equal for Aerofoils.
The coefficient in algebra is the number before a letter with an exponent on it. The 3 is the coefficient in this example: 3x7
The coefficient is the numerical value attached to an unknown or a variable. Thus, the coefficient of 8x is 8.
If 'N' is the variable, then 6 is the coefficient.
The coefficient is 1.6
For cylinders coefficient of lift is approximately half of coefficient of drag while they are equal for Aerofoils.
coefficient of drag in 0 lift
The F-18 Hornet has a maximum lift coefficient of around 2.5 in clean configuration.
0.08
0.016
The zero lift drag coefficient of a Boeing 747 is approximately 0.022. This value represents the drag force experienced by the aircraft when it is not generating lift.
0.032
I'm not sure if I understand you question but Lift Coefficient refers to the lifting force of a wing. Engines do not provide Lift; only Thrust.
A wing generates lift through a combination of factors including its shape, angle of attack, airspeed, and air density. The lift produced is proportional to the wing's surface area, the coefficient of lift, and the square of the airspeed. The exact amount of lift can vary depending on these factors and is typically calculated using aerodynamic theory.
The coefficient of lift of the V-22 Osprey aircraft varies depending on its flight conditions and configuration. However, typical values range between 0.5 and 1.0.
For no lift, The induced drag will be zero. However, there will still be drag due to viscous forces and pressure forces.
LIft = coefficient times density times velocity squared times wing area divided by 2 drag= coefficient times density times velocity squared over 2 times reference area