- #1
aaronmorg
- 6
- 0
I am working on my semester project and have come across a hitch. I am trying to find the Lift Force of my wing using the following equation
FL=CL P A (v2/2)
Where:
FL is Lift Force
CL is Coefficient of Lift (I think)
P is the density of the fluid (Air)
A is the Area
V is Velocity
The only portion I cannot find is Velocity. I cannot, for the life of me, figured out Velocity when given force and mass.
I have a 3.33 lbf and a 27.999g aircraft.
Can someone please help me.
Equation so far:
FL=(.76764)(.076)(56.55)(V2/2)
FL=CL P A (v2/2)
Where:
FL is Lift Force
CL is Coefficient of Lift (I think)
P is the density of the fluid (Air)
A is the Area
V is Velocity
The only portion I cannot find is Velocity. I cannot, for the life of me, figured out Velocity when given force and mass.
I have a 3.33 lbf and a 27.999g aircraft.
Can someone please help me.
Equation so far:
FL=(.76764)(.076)(56.55)(V2/2)