@@ -3,7 +3,6 @@ using VortexStepMethod
33using CSV
44using DataFrames
55using LinearAlgebra
6- using Plots
76
87# Create wing geometry
98wing = KiteWing (" data/HL5_ram_air_kite_body.obj" )
@@ -19,38 +18,6 @@ for (i, alpha) in enumerate(alphas)
1918 polars[i, :] .= [alpha, cd, cl, cm]
2019end
2120
22- # Plot polars directly
23- p = plot (layout= (2 ,2 ), size= (1000 ,1000 ))
24-
25- # CL vs alpha
26- plot! (p[1 ], rad2deg .(polars[:,1 ]), polars[:,3 ],
27- label= " CL" ,
28- xlabel= " Angle of Attack [deg]" ,
29- ylabel= " CL" ,
30- title= " Lift Coefficient" )
31-
32- # CD vs alpha
33- plot! (p[2 ], rad2deg .(polars[:,1 ]), polars[:,2 ],
34- label= " CD" ,
35- xlabel= " Angle of Attack [deg]" ,
36- ylabel= " CD" ,
37- title= " Drag Coefficient" )
38-
39- # CM vs alpha
40- plot! (p[3 ], rad2deg .(polars[:,1 ]), polars[:,4 ],
41- label= " CM" ,
42- xlabel= " Angle of Attack [deg]" ,
43- ylabel= " CM" ,
44- title= " Moment Coefficient" )
45-
46- # CL vs CD
47- plot! (p[4 ], polars[:,2 ], polars[:,3 ],
48- label= " Polar" ,
49- xlabel= " CD" ,
50- ylabel= " CL" ,
51- title= " Lift-Drag Polar" )
52- display (p)
53-
5421for gamma in range (wing. gamma_tip - wing. gamma_tip/ 10 , - wing. gamma_tip + wing. gamma_tip/ 10 , 20 )
5522 add_section! (wing, gamma, (" polar_data" , polars))
5623end
0 commit comments