function [CL_adot_w, CL_adot_h,CLadot]=Cladot2(XacP_c_w,CLa_w,CLa_h,eta_h,V_h,deda)

%CLg=0.984889; %a guess from fig 6.1, the figure isn't valid for our non-triangular wing
CL_adot_w=1.5*(XacP_c_w)*CLa_w    %+3*CLg %eqn 6.2
CL_adot_h=2*CLa_h*eta_h*V_h*deda; %eqn 6.3

CLadot=CL_adot_w+CL_adot_h	%eqn 6.1

return 