rubai
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I want to make a quad rotor UAV. i studied a lot but i did not find how static thrust is being calculated. In physics forum i have found an equation which is given below but i can not understand what is 'frac' and 'rho'.
Equation is:
T=\frac{c_T}{c_p}\frac{P}{nD}
Where:
P = power (ft-lb/s or kWW)
T = Thrust (lb or kN)
D = Prop Diameter (ft or m)
n = rotation speed (rev/s)
c_P = Power coefficient
c_T = Thrust coefficient
And:
c_P=\frac{P}{\rho n^3 D^5}
c_T = \frac{T}{\rho n^2 D^4}
Equation is:
T=\frac{c_T}{c_p}\frac{P}{nD}
Where:
P = power (ft-lb/s or kWW)
T = Thrust (lb or kN)
D = Prop Diameter (ft or m)
n = rotation speed (rev/s)
c_P = Power coefficient
c_T = Thrust coefficient
And:
c_P=\frac{P}{\rho n^3 D^5}
c_T = \frac{T}{\rho n^2 D^4}