Nblades = 3 
Rhub = 18/1000
Rtip = 75/1000
betaBlade = 27.705np.pi/180
Lchord = 23.086/1000

Mprop = 21.12/1000 
Mpayload = 1.61/1000
Mvehicle = Mprop + Mpayload
Rtip = 75/1000
Iprop = 1/2*Mprop*Rtip**2
Aprop = np.pi*Rtip**2

g = 9.81
rhoAir = 1.225
k = 0.945

gamma = np.arctan2( Vair , OmegaProp*r )
alpha = beta - gamma
cL,cD = liftDragCoefficients(alpha)
cT = cL*np.cos(gamma) - cD*np.sin(gamma)
cQ = cD*np.cos(gamma) + cL*np.sin(gamma)
fT = (0.5*rhoAir*Nblades)*L*cT*( Vair**2 + OmegaProp**2*r**2 )
fQ = (0.5*rhoAir*Nblades)*L*cQ*( Vair**2 + OmegaProp**2*r**2 )*r*k

Nblades = 4; 
Rhub = 40/1000; 
Rtip = 98/1000; s
betaBlade = 30pi/180; 
Lchord = 18.5/1000; 

Mprop = 45/1000; 
Mpayload = 1.61/1000;
Mvehicle = Mprop + Mpayload;
Rtip = 98/1000; 
Iprop = 1/2MpropRtip^2; 
Aprop = pi*Rtip^2;

Nblades = 5;
Rhub = 48/1000; 
Rtip = 88/1000; 
betaBlade = 30pi/180; 
Lchord = 20/1000;

Mprop = 45/1000; 
Mpayload = 1.61/1000; 
Mvehicle = Mprop + Mpayload;
Rtip = 88/1000; 
Iprop = 1/2MpropRtip^2;
Aprop = pi*Rtip^2;