% Script to test interlim2
% tc_w				wing thickness to chord ratio
tc_w=.12
McosLambda_c4 = .69
tc_w_tab = [.07,.08,.09,.10,.12,.14,.16]	% Taper ratio from fig.(8.42)
McosLambda_c4_tab = [0.3,.35,.4,.45,.5,.55,.6,.65,.7,.75,.8,.85,.9];		% Sweep chord angle from fig.(8.42)

PrandetlGlaurtScale_tab(:,:) =...
                  [1	1	1	1	1	1	1
                  1	1	1	1	1	1	1
                  1	1	1	1	1	1	1
                  1	1	1	1	1	1	0.96
                  1	1	1	1	1	1	0.88
                  1	1	1	1	1	0.96	0.68
                  1	1	1	1	0.99	0.8	0.4
                  1	1	1	1	0.91	0.51	-0.09
                  1	1	1	1	0.6	0.011	-1
                  1	1	1	0.87	-0.21	NaN	NaN
                  1	0.95	0.82	0.092	NaN	NaN	NaN
                  0.95	0.68	0.12	NaN	NaN	NaN	NaN
                  0.87	NaN	NaN	NaN	NaN	NaN	NaN];	% Mach number correction for zero-lift angle AOA of cambered airfoils Ref.(3) fig.(8.42)
              
 PrandetlGlaurtScale_tab
 McosLambda_c4_tab'
 PrandetlGlaurtScale = interlim2(tc_w_tab,McosLambda_c4_tab,PrandetlGlaurtScale_tab,tc_w,McosLambda_c4)
 plot(McosLambda_c4_tab,PrandetlGlaurtScale_tab)
 hold on; plot(McosLambda_c4,PrandetlGlaurtScale,'rx'); hold off