SG6042 (sg6042-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 500,000 Max Cl/Cd: 123.58 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6042-il-500000.txt Download as CSV file: xf-sg6042-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3107 0.08689 0.08466 -0.0561 0.9887 0.0192
-8.250 -0.2975 0.08064 0.07842 -0.0643 0.9858 0.0193
-8.000 -0.2887 0.07693 0.07472 -0.0665 0.9828 0.0198
-7.750 -0.2752 0.07407 0.07187 -0.0693 0.9781 0.0202
-7.500 -0.2585 0.06962 0.06742 -0.0759 0.9744 0.0206
-7.250 -0.2422 0.06475 0.06255 -0.0834 0.9678 0.0217
-7.000 -0.2194 0.05708 0.05480 -0.0962 0.9627 0.0223
-6.750 -0.2042 0.04331 0.04059 -0.1108 0.9540 0.0245
-6.500 -0.1791 0.04299 0.04032 -0.1121 0.9517 0.0254
-6.250 -0.1509 0.03934 0.03651 -0.1162 0.9495 0.0267
-6.000 -0.1382 0.02299 0.01868 -0.1203 0.9426 0.0189
-5.750 -0.1141 0.01921 0.01437 -0.1208 0.9383 0.0184
-5.500 -0.0835 0.01686 0.01159 -0.1217 0.9359 0.0186
-5.250 -0.0503 0.01550 0.00989 -0.1229 0.9341 0.0194
-5.000 -0.0180 0.01406 0.00838 -0.1242 0.9324 0.0207
-4.750 0.0041 0.01339 0.00764 -0.1230 0.9261 0.0215
-4.500 0.0346 0.01260 0.00674 -0.1235 0.9227 0.0224
-4.250 0.0665 0.01189 0.00593 -0.1242 0.9200 0.0233
-4.000 0.0957 0.01118 0.00516 -0.1245 0.9164 0.0247
-3.750 0.1211 0.01077 0.00475 -0.1241 0.9107 0.0267
-3.500 0.1512 0.01034 0.00428 -0.1244 0.9066 0.0284
-3.250 0.1826 0.00986 0.00374 -0.1251 0.9032 0.0309
-3.000 0.2073 0.00959 0.00348 -0.1244 0.8968 0.0353
-2.750 0.2361 0.00917 0.00312 -0.1245 0.8920 0.0530
-2.500 0.2668 0.00888 0.00288 -0.1251 0.8881 0.0812
-2.250 0.2917 0.00868 0.00277 -0.1245 0.8817 0.1070
-2.000 0.3200 0.00836 0.00261 -0.1246 0.8763 0.1635
-1.750 0.3471 0.00780 0.00249 -0.1248 0.8708 0.3080
-1.500 0.3711 0.00711 0.00247 -0.1244 0.8640 0.5259
-1.250 0.3981 0.00680 0.00249 -0.1241 0.8588 0.6564
-1.000 0.4232 0.00671 0.00251 -0.1233 0.8520 0.7099
-0.750 0.4502 0.00664 0.00248 -0.1228 0.8455 0.7460
-0.500 0.4761 0.00658 0.00247 -0.1221 0.8383 0.7793
-0.250 0.5018 0.00652 0.00244 -0.1213 0.8306 0.8093
0.000 0.5272 0.00648 0.00244 -0.1205 0.8234 0.8362
0.250 0.5512 0.00642 0.00243 -0.1194 0.8156 0.8667
0.500 0.5731 0.00636 0.00242 -0.1176 0.8074 0.9033
0.750 0.5969 0.00627 0.00236 -0.1162 0.7986 0.9464
1.000 0.6382 0.00621 0.00229 -0.1190 0.7890 0.9884
1.250 0.6691 0.00624 0.00224 -0.1196 0.7789 1.0000
1.500 0.6952 0.00629 0.00222 -0.1192 0.7672 1.0000
1.750 0.7208 0.00634 0.00223 -0.1187 0.7548 1.0000
2.000 0.7466 0.00640 0.00224 -0.1182 0.7417 1.0000
2.250 0.7722 0.00648 0.00226 -0.1177 0.7270 1.0000
2.500 0.7973 0.00658 0.00229 -0.1170 0.7096 1.0000
2.750 0.8218 0.00671 0.00232 -0.1162 0.6899 1.0000
3.000 0.8461 0.00686 0.00239 -0.1154 0.6686 1.0000
3.250 0.8700 0.00704 0.00247 -0.1145 0.6469 1.0000
3.500 0.8933 0.00725 0.00259 -0.1135 0.6212 1.0000
3.750 0.9158 0.00749 0.00272 -0.1124 0.5937 1.0000
4.000 0.9376 0.00778 0.00287 -0.1111 0.5637 1.0000
4.250 0.9584 0.00812 0.00306 -0.1097 0.5294 1.0000
4.500 0.9783 0.00851 0.00328 -0.1082 0.4922 1.0000
4.750 0.9981 0.00893 0.00352 -0.1067 0.4533 1.0000
5.000 1.0174 0.00939 0.00380 -0.1051 0.4142 1.0000
5.250 1.0370 0.00986 0.00410 -0.1036 0.3765 1.0000
5.500 1.0562 0.01036 0.00441 -0.1021 0.3403 1.0000
5.750 1.0758 0.01086 0.00474 -0.1007 0.3051 1.0000
6.000 1.0954 0.01135 0.00509 -0.0993 0.2736 1.0000
6.250 1.1150 0.01184 0.00545 -0.0979 0.2452 1.0000
6.500 1.1344 0.01235 0.00582 -0.0965 0.2195 1.0000
6.750 1.1539 0.01284 0.00621 -0.0951 0.1956 1.0000
7.000 1.1728 0.01335 0.00662 -0.0937 0.1751 1.0000
7.250 1.1914 0.01382 0.00702 -0.0921 0.1577 1.0000
7.500 1.2095 0.01430 0.00744 -0.0905 0.1427 1.0000
7.750 1.2273 0.01480 0.00788 -0.0888 0.1293 1.0000
8.000 1.2448 0.01531 0.00835 -0.0871 0.1176 1.0000
8.250 1.2615 0.01587 0.00886 -0.0853 0.1069 1.0000
8.500 1.2796 0.01635 0.00933 -0.0838 0.0983 1.0000
8.750 1.2968 0.01688 0.00987 -0.0821 0.0907 1.0000
9.000 1.3127 0.01748 0.01044 -0.0803 0.0835 1.0000
9.250 1.3299 0.01800 0.01101 -0.0787 0.0780 1.0000
9.500 1.3457 0.01862 0.01161 -0.0769 0.0723 1.0000
9.750 1.3611 0.01926 0.01228 -0.0751 0.0677 1.0000
10.000 1.3775 0.01983 0.01290 -0.0735 0.0633 1.0000
10.250 1.3884 0.02077 0.01382 -0.0712 0.0587 1.0000
10.500 1.4058 0.02128 0.01442 -0.0698 0.0559 1.0000
10.750 1.4204 0.02199 0.01516 -0.0681 0.0525 1.0000
11.000 1.4288 0.02312 0.01629 -0.0657 0.0485 1.0000
11.250 1.4452 0.02373 0.01701 -0.0643 0.0461 1.0000
11.500 1.4585 0.02456 0.01788 -0.0626 0.0433 1.0000
11.750 1.4645 0.02592 0.01926 -0.0602 0.0402 1.0000
12.000 1.4768 0.02686 0.02030 -0.0586 0.0383 1.0000
12.250 1.4889 0.02783 0.02135 -0.0570 0.0361 1.0000
12.500 1.4978 0.02906 0.02262 -0.0552 0.0341 1.0000
12.750 1.4972 0.03109 0.02471 -0.0526 0.0321 1.0000
13.000 1.5088 0.03219 0.02593 -0.0512 0.0310 1.0000
13.250 1.5179 0.03350 0.02734 -0.0498 0.0296 1.0000
13.500 1.5258 0.03495 0.02886 -0.0484 0.0283 1.0000
13.750 1.5298 0.03679 0.03075 -0.0468 0.0272 1.0000
14.000 1.5268 0.03935 0.03340 -0.0450 0.0261 1.0000
14.250 1.5290 0.04152 0.03569 -0.0437 0.0254 1.0000
14.500 1.5350 0.04337 0.03767 -0.0427 0.0247 1.0000
14.750 1.5393 0.04546 0.03987 -0.0418 0.0239 1.0000
15.000 1.5425 0.04773 0.04226 -0.0411 0.0231 1.0000
15.250 1.5447 0.05017 0.04479 -0.0406 0.0224 1.0000
15.500 1.5439 0.05308 0.04780 -0.0402 0.0219 1.0000
15.750 1.5403 0.05643 0.05122 -0.0400 0.0212 1.0000
16.000 1.5303 0.06075 0.05566 -0.0400 0.0207 1.0000
16.250 1.5279 0.06428 0.05933 -0.0404 0.0203 1.0000
16.500 1.5280 0.06761 0.06281 -0.0410 0.0199 1.0000
16.750 1.5251 0.07148 0.06683 -0.0418 0.0195 1.0000
17.000 1.5211 0.07565 0.07114 -0.0429 0.0191 1.0000
17.250 1.5161 0.08008 0.07571 -0.0443 0.0187 1.0000
17.500 1.5101 0.08483 0.08059 -0.0460 0.0184 1.0000
17.750 1.5034 0.08984 0.08573 -0.0480 0.0181 1.0000
18.000 1.4957 0.09514 0.09115 -0.0503 0.0178 1.0000
18.250 1.4869 0.10074 0.09689 -0.0529 0.0176 1.0000
18.500 1.4775 0.10656 0.10283 -0.0557 0.0174 1.0000
18.750 1.4677 0.11259 0.10897 -0.0587 0.0171 1.0000
19.000 1.4575 0.11873 0.11523 -0.0620 0.0169 1.0000
19.250 1.4468 0.12500 0.12161 -0.0654 0.0167 1.0000
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Polar data table (+)
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