L=CL×0.5×ρ×V^2×S
I want to design a V tail. The moment of the wing turned out to be -9.3 Nm. The tail needs to balance this moment. I'm thinking of taking the tail moment arm as 0.5-0.6m. I calculate a lift force with the formula I wrote, but my lift force turns out to be very low. Is the formula wrong or am I making a mistake somewhere else? My root chord length is 0.2m, my end chord length is 0.09m
I want to design a V tail. The moment of the wing turned out to be -9.3 Nm. The tail needs to balance this moment. I'm thinking of taking the tail moment arm as 0.5-0.6m. I calculate a lift force with the formula I wrote, but my lift force turns out to be very low. Is the formula wrong or am I making a mistake somewhere else? My root chord length is 0.2m, my end chord length is 0.09m