function [CLa_w,Kwb,CLa_wb,CLa_h,CLa,CLa_v]=CLa2(AR_w,AR_h,AR_v_eff,Kap,Kap2,Lam2_w,Lam2_h,...
   Lam2_v,d,b_w,eta_h,S_h,S_w,deda,Beta)

% 3.2a CLa wing
CLa_w= 2*pi*(AR_w)/ (2+sqrt((AR_w*Beta/Kap)^2*(1+(tan(Lam2_w))^2/Beta^2)+4 )); %eqn 3.8
Kwb= (1-.25*(d/b_w)^2+.025*(d/b_w));	%eqn 3.7
CLa_wb = 0.02+Kwb*CLa_w;						%eqn 3.6

% 3.2b CLa horizontal tail

CLa_h= 2*pi*AR_h/(2+sqrt((AR_h*Beta/Kap2)^2*(1+(tan(Lam2_h))^2/Beta^2)+4 )); %eqn 3.8

%combine for CLa
CLa = CLa_wb + CLa_h*eta_h*(S_h/S_w)*(1-deda); %eqn 3.5

% CLa vertical tail
CLa_v= 2*pi*AR_v_eff / (2+sqrt((AR_v_eff*Beta/Kap)^2*(1+(tan(Lam2_v))^2/Beta^2)+4 ));

return 