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coefficient of drag in 0 lift
0.032
For cylinders coefficient of lift is approximately half of coefficient of drag while they are equal for Aerofoils.
17.4
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
The lift/drag coefficient of an Antonov An 225 is 19 with no change in the aerodynamics,Mach 4 mark,cruising altitude with the nett thrust payload of max.600 tonnes. Um more like 4.273 which is the inverse of the Thrust. Max load 200 ton, and a service ceiling of 11,000m
The production of lift creates induced drag. To create more lift, more airspeed is needed, and with airspeed, comes drag.
lift decrease and increase drag
Lift, thrust, drag, and gravity affects all flying objects and wildlife. The blades of the helicopter provide lift, drag and thrust.
A higher angle of attack has an increase of both lift and drag.
0.08