SG6042 (sg6042-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 200,000 Max Cl/Cd: 88.96 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6042-il-200000.txt Download as CSV file: xf-sg6042-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3914 0.09911 0.09589 -0.0258 1.0000 0.0415
-7.750 -0.4016 0.09727 0.09410 -0.0243 1.0000 0.0421
-7.500 -0.4135 0.09549 0.09238 -0.0226 1.0000 0.0427
-7.250 -0.4089 0.09116 0.08807 -0.0305 0.9947 0.0447
-7.000 -0.3859 0.08203 0.07884 -0.0543 0.9849 0.0457
-6.750 -0.3788 0.07601 0.07282 -0.0570 0.9794 0.0464
-6.500 -0.3646 0.07372 0.07059 -0.0545 0.9767 0.0475
-6.250 -0.3421 0.07016 0.06700 -0.0582 0.9736 0.0490
-6.000 -0.3273 0.06608 0.06286 -0.0622 0.9669 0.0510
-5.750 -0.2889 0.05680 0.05285 -0.0794 0.9604 0.0569
-5.500 -0.2782 0.05272 0.04891 -0.0788 0.9551 0.0581
-5.250 -0.2562 0.05009 0.04630 -0.0800 0.9510 0.0600
-5.000 -0.2122 0.04780 0.04324 -0.0863 0.9474 0.0689
-4.750 -0.1991 0.04195 0.03751 -0.0873 0.9425 0.0713
-4.500 -0.1745 0.04010 0.03569 -0.0881 0.9380 0.0765
-4.250 -0.1322 0.03009 0.02434 -0.0919 0.9358 0.0482
-4.000 -0.0942 0.02558 0.01909 -0.0936 0.9343 0.0404
-3.750 -0.0550 0.02351 0.01660 -0.0957 0.9328 0.0413
-3.500 -0.0338 0.02255 0.01540 -0.0943 0.9260 0.0433
-3.250 0.0009 0.02115 0.01372 -0.0953 0.9228 0.0443
-3.000 0.0384 0.01996 0.01235 -0.0969 0.9205 0.0462
-2.750 0.0774 0.01893 0.01138 -0.0992 0.9188 0.0525
-2.500 0.0995 0.01840 0.01079 -0.0979 0.9118 0.0573
-2.250 0.1339 0.01750 0.00995 -0.0992 0.9081 0.0707
-2.000 0.1728 0.01668 0.00928 -0.1014 0.9057 0.1114
-1.750 0.2128 0.01577 0.00882 -0.1042 0.9039 0.2022
-1.500 0.2290 0.01449 0.00904 -0.1026 0.8966 0.5925
-1.250 0.2569 0.01403 0.00903 -0.1016 0.8926 0.7550
-1.000 0.2899 0.01364 0.00877 -0.1015 0.8901 0.8330
-0.750 0.3192 0.01335 0.00854 -0.1007 0.8864 0.9001
-0.500 0.3678 0.01315 0.00831 -0.1045 0.8818 1.0000
-0.250 0.4074 0.01295 0.00798 -0.1068 0.8778 1.0000
0.000 0.4502 0.01267 0.00759 -0.1096 0.8751 1.0000
0.250 0.4813 0.01259 0.00742 -0.1101 0.8688 1.0000
0.500 0.5159 0.01239 0.00714 -0.1112 0.8626 1.0000
0.750 0.5582 0.01204 0.00671 -0.1137 0.8591 1.0000
1.000 0.5835 0.01203 0.00665 -0.1130 0.8497 1.0000
1.250 0.6221 0.01174 0.00630 -0.1147 0.8446 1.0000
1.500 0.6489 0.01169 0.00622 -0.1142 0.8352 1.0000
1.750 0.6862 0.01141 0.00588 -0.1156 0.8285 1.0000
2.000 0.7120 0.01135 0.00581 -0.1148 0.8174 1.0000
2.250 0.7423 0.01122 0.00564 -0.1149 0.8076 1.0000
2.500 0.7749 0.01103 0.00539 -0.1153 0.7975 1.0000
2.750 0.8004 0.01097 0.00534 -0.1145 0.7842 1.0000
3.000 0.8265 0.01093 0.00527 -0.1138 0.7707 1.0000
3.250 0.8529 0.01087 0.00520 -0.1131 0.7560 1.0000
3.500 0.8792 0.01083 0.00514 -0.1124 0.7398 1.0000
3.750 0.9060 0.01080 0.00506 -0.1118 0.7219 1.0000
4.000 0.9296 0.01085 0.00509 -0.1106 0.7006 1.0000
4.250 0.9547 0.01092 0.00511 -0.1097 0.6786 1.0000
4.500 0.9779 0.01106 0.00519 -0.1086 0.6533 1.0000
4.750 1.0008 0.01125 0.00528 -0.1073 0.6250 1.0000
5.000 1.0222 0.01152 0.00542 -0.1058 0.5927 1.0000
5.250 1.0422 0.01186 0.00563 -0.1041 0.5571 1.0000
5.500 1.0603 0.01229 0.00588 -0.1021 0.5174 1.0000
5.750 1.0769 0.01280 0.00620 -0.0999 0.4760 1.0000
6.000 1.0921 0.01339 0.00657 -0.0975 0.4332 1.0000
6.250 1.1066 0.01403 0.00702 -0.0951 0.3907 1.0000
6.500 1.1204 0.01472 0.00751 -0.0926 0.3499 1.0000
6.750 1.1337 0.01546 0.00805 -0.0901 0.3122 1.0000
7.000 1.1472 0.01622 0.00863 -0.0877 0.2775 1.0000
7.250 1.1599 0.01698 0.00924 -0.0852 0.2469 1.0000
7.500 1.1719 0.01778 0.00989 -0.0827 0.2211 1.0000
7.750 1.1858 0.01855 0.01058 -0.0805 0.1987 1.0000
8.000 1.1989 0.01939 0.01131 -0.0782 0.1801 1.0000
8.250 1.2121 0.02025 0.01210 -0.0760 0.1643 1.0000
8.500 1.2260 0.02110 0.01291 -0.0739 0.1507 1.0000
8.750 1.2404 0.02195 0.01376 -0.0720 0.1388 1.0000
9.000 1.2542 0.02287 0.01467 -0.0700 0.1286 1.0000
9.250 1.2666 0.02393 0.01565 -0.0680 0.1197 1.0000
9.500 1.2817 0.02473 0.01655 -0.0663 0.1114 1.0000
9.750 1.2948 0.02583 0.01764 -0.0645 0.1043 1.0000
10.000 1.3085 0.02673 0.01859 -0.0627 0.0976 1.0000
10.250 1.3218 0.02795 0.01982 -0.0610 0.0918 1.0000
10.500 1.3352 0.02890 0.02088 -0.0593 0.0862 1.0000
10.750 1.3483 0.03036 0.02228 -0.0578 0.0810 1.0000
11.000 1.3609 0.03133 0.02344 -0.0561 0.0766 1.0000
11.250 1.3719 0.03248 0.02463 -0.0544 0.0723 1.0000
11.500 1.3854 0.03408 0.02627 -0.0530 0.0681 1.0000
11.750 1.3956 0.03529 0.02765 -0.0512 0.0643 1.0000
12.000 1.4049 0.03663 0.02903 -0.0496 0.0609 1.0000
12.250 1.4185 0.03855 0.03100 -0.0484 0.0576 1.0000
12.500 1.4270 0.04011 0.03279 -0.0467 0.0549 1.0000
12.750 1.4350 0.04170 0.03448 -0.0452 0.0524 1.0000
13.000 1.4443 0.04345 0.03623 -0.0440 0.0500 1.0000
13.250 1.4541 0.04588 0.03883 -0.0427 0.0478 1.0000
13.500 1.4577 0.04796 0.04117 -0.0411 0.0462 1.0000
13.750 1.4612 0.05024 0.04367 -0.0397 0.0447 1.0000
14.000 1.4644 0.05258 0.04618 -0.0384 0.0434 1.0000
14.250 1.4678 0.05494 0.04866 -0.0373 0.0422 1.0000
14.500 1.4726 0.05748 0.05128 -0.0365 0.0410 1.0000
14.750 1.4735 0.06189 0.05587 -0.0357 0.0398 1.0000
15.000 1.4631 0.06530 0.05956 -0.0348 0.0394 1.0000
15.250 1.4513 0.06925 0.06380 -0.0343 0.0389 1.0000
15.500 1.4374 0.07368 0.06850 -0.0343 0.0385 1.0000
15.750 1.4217 0.07867 0.07375 -0.0349 0.0382 1.0000
16.000 1.4036 0.08432 0.07967 -0.0362 0.0379 1.0000
16.250 1.3831 0.09067 0.08628 -0.0384 0.0377 1.0000
16.500 1.3598 0.09798 0.09384 -0.0416 0.0376 1.0000
16.750 1.3333 0.10642 0.10253 -0.0460 0.0377 1.0000
17.000 1.3024 0.11640 0.11276 -0.0519 0.0379 1.0000
17.250 1.2664 0.12845 0.12503 -0.0598 0.0384 1.0000
17.500 1.2225 0.14369 0.14045 -0.0702 0.0392 1.0000
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