SG6042 (sg6042-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 500,000 Max Cl/Cd: 106.28 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6042-il-500000-n5.txt Download as CSV file: xf-sg6042-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6042
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2887 0.08517 0.08278 -0.0628 0.9858 0.0075
-8.750 -0.2826 0.08027 0.07789 -0.0670 0.9819 0.0077
-8.500 -0.2751 0.07560 0.07324 -0.0714 0.9771 0.0080
-8.250 -0.2672 0.06936 0.06700 -0.0786 0.9731 0.0082
-8.000 -0.2684 0.06290 0.06057 -0.0854 0.9621 0.0084
-7.750 -0.3161 0.02319 0.01915 -0.1180 0.9367 0.0084
-7.500 -0.2913 0.01955 0.01486 -0.1196 0.9332 0.0088
-7.250 -0.2670 0.01796 0.01289 -0.1197 0.9278 0.0091
-7.000 -0.2404 0.01659 0.01133 -0.1203 0.9233 0.0095
-6.750 -0.2105 0.01575 0.01036 -0.1212 0.9199 0.0098
-6.500 -0.1822 0.01498 0.00945 -0.1216 0.9158 0.0102
-6.250 -0.1555 0.01426 0.00859 -0.1217 0.9103 0.0107
-6.000 -0.1264 0.01364 0.00782 -0.1221 0.9059 0.0114
-5.750 -0.0971 0.01320 0.00723 -0.1225 0.9017 0.0120
-5.500 -0.0719 0.01239 0.00636 -0.1222 0.8957 0.0126
-5.250 -0.0437 0.01189 0.00579 -0.1224 0.8909 0.0132
-5.000 -0.0159 0.01144 0.00527 -0.1225 0.8862 0.0138
-4.750 0.0106 0.01104 0.00480 -0.1223 0.8806 0.0144
-4.500 0.0387 0.01070 0.00437 -0.1223 0.8757 0.0151
-4.250 0.0661 0.01029 0.00392 -0.1223 0.8711 0.0162
-4.000 0.0929 0.01001 0.00361 -0.1221 0.8655 0.0172
-3.750 0.1208 0.00975 0.00329 -0.1221 0.8606 0.0182
-3.500 0.1486 0.00953 0.00301 -0.1221 0.8557 0.0192
-3.250 0.1754 0.00930 0.00276 -0.1219 0.8498 0.0212
-3.000 0.2034 0.00910 0.00255 -0.1218 0.8445 0.0252
-2.750 0.2306 0.00890 0.00238 -0.1217 0.8391 0.0353
-2.500 0.2579 0.00873 0.00224 -0.1216 0.8333 0.0487
-2.250 0.2859 0.00860 0.00211 -0.1216 0.8282 0.0620
-2.000 0.3129 0.00846 0.00201 -0.1214 0.8219 0.0786
-1.750 0.3402 0.00830 0.00192 -0.1213 0.8151 0.1074
-1.500 0.3672 0.00809 0.00184 -0.1212 0.8085 0.1526
-1.250 0.3938 0.00777 0.00177 -0.1211 0.8016 0.2417
-1.000 0.4205 0.00742 0.00171 -0.1211 0.7949 0.3535
-0.750 0.4465 0.00708 0.00169 -0.1209 0.7867 0.4744
-0.500 0.4723 0.00682 0.00172 -0.1205 0.7779 0.5867
-0.250 0.4983 0.00672 0.00174 -0.1200 0.7680 0.6494
0.000 0.5245 0.00666 0.00176 -0.1195 0.7580 0.6890
0.250 0.5504 0.00663 0.00179 -0.1189 0.7479 0.7290
0.500 0.5753 0.00659 0.00182 -0.1181 0.7358 0.7712
0.750 0.5995 0.00657 0.00186 -0.1171 0.7214 0.8089
1.000 0.6229 0.00657 0.00189 -0.1159 0.7062 0.8428
1.250 0.6456 0.00659 0.00192 -0.1145 0.6896 0.8744
1.500 0.6673 0.00664 0.00195 -0.1129 0.6688 0.9048
1.750 0.6909 0.00672 0.00198 -0.1118 0.6476 0.9380
2.000 0.7245 0.00684 0.00201 -0.1130 0.6233 0.9855
2.250 0.7493 0.00705 0.00208 -0.1124 0.5981 1.0000
2.500 0.7721 0.00731 0.00219 -0.1114 0.5687 1.0000
2.750 0.7943 0.00761 0.00232 -0.1103 0.5353 1.0000
3.000 0.8163 0.00793 0.00247 -0.1091 0.5008 1.0000
3.250 0.8386 0.00825 0.00264 -0.1081 0.4695 1.0000
3.500 0.8610 0.00858 0.00282 -0.1071 0.4390 1.0000
3.750 0.8830 0.00894 0.00303 -0.1060 0.4071 1.0000
4.000 0.9049 0.00931 0.00324 -0.1050 0.3755 1.0000
4.250 0.9269 0.00969 0.00347 -0.1039 0.3448 1.0000
4.500 0.9482 0.01012 0.00374 -0.1028 0.3120 1.0000
4.750 0.9697 0.01053 0.00401 -0.1017 0.2823 1.0000
5.000 0.9913 0.01094 0.00428 -0.1007 0.2544 1.0000
5.250 1.0131 0.01134 0.00456 -0.0997 0.2305 1.0000
5.500 1.0346 0.01175 0.00487 -0.0986 0.2078 1.0000
5.750 1.0562 0.01215 0.00517 -0.0976 0.1881 1.0000
6.000 1.0778 0.01254 0.00548 -0.0966 0.1705 1.0000
6.250 1.0992 0.01292 0.00581 -0.0955 0.1555 1.0000
6.500 1.1207 0.01330 0.00613 -0.0945 0.1431 1.0000
6.750 1.1415 0.01369 0.00648 -0.0934 0.1308 1.0000
7.000 1.1614 0.01410 0.00683 -0.0920 0.1194 1.0000
7.250 1.1812 0.01448 0.00720 -0.0907 0.1097 1.0000
7.500 1.2009 0.01486 0.00757 -0.0893 0.1020 1.0000
7.750 1.2195 0.01531 0.00798 -0.0878 0.0937 1.0000
8.000 1.2388 0.01571 0.00839 -0.0864 0.0867 1.0000
8.250 1.2571 0.01617 0.00884 -0.0849 0.0800 1.0000
8.500 1.2756 0.01662 0.00929 -0.0834 0.0735 1.0000
8.750 1.2935 0.01711 0.00977 -0.0819 0.0682 1.0000
9.000 1.3114 0.01758 0.01027 -0.0804 0.0633 1.0000
9.250 1.3282 0.01814 0.01081 -0.0788 0.0585 1.0000
9.500 1.3459 0.01862 0.01134 -0.0773 0.0549 1.0000
9.750 1.3622 0.01920 0.01192 -0.0757 0.0510 1.0000
10.000 1.3783 0.01979 0.01256 -0.0740 0.0477 1.0000
10.250 1.3946 0.02036 0.01318 -0.0725 0.0449 1.0000
10.500 1.4098 0.02103 0.01386 -0.0708 0.0420 1.0000
10.750 1.4240 0.02175 0.01462 -0.0690 0.0394 1.0000
11.000 1.4393 0.02240 0.01534 -0.0675 0.0370 1.0000
11.250 1.4531 0.02317 0.01614 -0.0658 0.0345 1.0000
11.500 1.4653 0.02406 0.01707 -0.0640 0.0322 1.0000
11.750 1.4792 0.02484 0.01792 -0.0624 0.0306 1.0000
12.000 1.4917 0.02572 0.01887 -0.0607 0.0287 1.0000
12.250 1.5029 0.02673 0.01992 -0.0590 0.0269 1.0000
12.500 1.5132 0.02782 0.02107 -0.0573 0.0254 1.0000
12.750 1.5243 0.02887 0.02222 -0.0557 0.0242 1.0000
13.000 1.5341 0.03004 0.02347 -0.0541 0.0229 1.0000
13.250 1.5428 0.03134 0.02482 -0.0525 0.0218 1.0000
13.500 1.5494 0.03284 0.02639 -0.0508 0.0206 1.0000
13.750 1.5573 0.03426 0.02791 -0.0494 0.0199 1.0000
14.000 1.5647 0.03576 0.02952 -0.0480 0.0191 1.0000
14.250 1.5712 0.03738 0.03123 -0.0467 0.0183 1.0000
14.500 1.5763 0.03918 0.03312 -0.0454 0.0175 1.0000
14.750 1.5794 0.04123 0.03524 -0.0442 0.0167 1.0000
15.000 1.5805 0.04354 0.03765 -0.0432 0.0161 1.0000
15.250 1.5844 0.04567 0.03990 -0.0423 0.0156 1.0000
15.500 1.5862 0.04809 0.04245 -0.0416 0.0153 1.0000
15.750 1.5889 0.05049 0.04496 -0.0412 0.0146 1.0000
16.000 1.5889 0.05331 0.04790 -0.0408 0.0142 1.0000
16.250 1.5879 0.05638 0.05108 -0.0407 0.0138 1.0000
16.500 1.5854 0.05977 0.05458 -0.0409 0.0134 1.0000
16.750 1.5809 0.06357 0.05850 -0.0414 0.0131 1.0000
17.000 1.5740 0.06787 0.06293 -0.0422 0.0129 1.0000
17.250 1.5649 0.07273 0.06792 -0.0435 0.0126 1.0000
17.500 1.5580 0.07743 0.07278 -0.0450 0.0125 1.0000
17.750 1.5507 0.08234 0.07784 -0.0467 0.0123 1.0000
18.000 1.5412 0.08780 0.08346 -0.0488 0.0121 1.0000
18.250 1.5305 0.09365 0.08946 -0.0513 0.0120 1.0000
18.500 1.5179 0.10001 0.09598 -0.0543 0.0118 1.0000
18.750 1.5044 0.10671 0.10283 -0.0576 0.0116 1.0000
19.000 1.4896 0.11381 0.11009 -0.0613 0.0115 1.0000
19.250 1.4737 0.12130 0.11773 -0.0653 0.0114 1.0000
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