SG6043 (sg6043-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6043 (sg6043-il) Reynolds number: 100,000 Max Cl/Cd: 65.6 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6043-il-100000-n5.txt Download as CSV file: xf-sg6043-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6043
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2183 0.10267 0.09778 -0.0635 0.9637 0.0521
-7.500 -0.2198 0.10035 0.09551 -0.0666 0.9550 0.0524
-7.250 -0.2140 0.09712 0.09230 -0.0715 0.9480 0.0526
-7.000 -0.2048 0.09318 0.08839 -0.0712 0.9429 0.0530
-6.750 -0.1889 0.08956 0.08476 -0.0704 0.9402 0.0538
-6.250 -0.1672 0.08330 0.07852 -0.0736 0.9285 0.0554
-6.000 -0.1487 0.07932 0.07452 -0.0785 0.9243 0.0563
-5.500 -0.1176 0.06711 0.06217 -0.0933 0.9102 0.0356
-5.250 -0.1044 0.06341 0.05843 -0.0964 0.9030 0.0349
-5.000 -0.0772 0.05789 0.05277 -0.1041 0.8978 0.0350
-4.750 -0.0410 0.05194 0.04660 -0.1127 0.8948 0.0347
-4.500 -0.0169 0.04715 0.04157 -0.1172 0.8885 0.0336
-4.250 0.0228 0.04027 0.03413 -0.1250 0.8845 0.0321
-4.000 0.0679 0.03439 0.02744 -0.1317 0.8824 0.0314
-3.750 0.1083 0.03121 0.02372 -0.1356 0.8806 0.0317
-3.500 0.1474 0.02923 0.02135 -0.1386 0.8790 0.0335
-3.250 0.1721 0.02777 0.01946 -0.1386 0.8727 0.0354
-3.000 0.2062 0.02609 0.01728 -0.1399 0.8692 0.0366
-2.750 0.2411 0.02486 0.01592 -0.1414 0.8666 0.0379
-2.500 0.2778 0.02378 0.01469 -0.1431 0.8646 0.0402
-2.250 0.3157 0.02279 0.01354 -0.1448 0.8631 0.0443
-2.000 0.3335 0.02261 0.01339 -0.1432 0.8547 0.0485
-1.750 0.3679 0.02186 0.01259 -0.1444 0.8516 0.0553
-1.500 0.4052 0.02116 0.01190 -0.1461 0.8493 0.0717
-1.250 0.4440 0.02053 0.01135 -0.1482 0.8475 0.1064
-1.000 0.4616 0.02048 0.01140 -0.1466 0.8387 0.1383
-0.750 0.4977 0.01983 0.01103 -0.1483 0.8355 0.2129
-0.500 0.5367 0.01882 0.01087 -0.1508 0.8334 0.4817
-0.250 0.5586 0.01853 0.01102 -0.1492 0.8274 0.6628
0.000 0.5753 0.01819 0.01098 -0.1461 0.8211 0.7989
0.250 0.6072 0.01769 0.01050 -0.1460 0.8176 1.0000
0.500 0.6323 0.01788 0.01054 -0.1455 0.8104 1.0000
0.750 0.6641 0.01790 0.01041 -0.1462 0.8049 1.0000
1.000 0.7035 0.01774 0.01010 -0.1481 0.8015 1.0000
1.250 0.7257 0.01797 0.01024 -0.1471 0.7929 1.0000
1.500 0.7604 0.01788 0.01006 -0.1481 0.7876 1.0000
1.750 0.7976 0.01772 0.00981 -0.1496 0.7831 1.0000
2.000 0.8191 0.01795 0.00999 -0.1484 0.7734 1.0000
2.250 0.8584 0.01771 0.00969 -0.1502 0.7688 1.0000
2.500 0.8784 0.01795 0.00991 -0.1486 0.7581 1.0000
2.750 0.9179 0.01768 0.00959 -0.1504 0.7526 1.0000
3.000 0.9374 0.01791 0.00982 -0.1487 0.7410 1.0000
3.250 0.9654 0.01793 0.00984 -0.1485 0.7314 1.0000
3.500 0.9979 0.01781 0.00969 -0.1490 0.7221 1.0000
3.750 1.0204 0.01794 0.00983 -0.1478 0.7096 1.0000
4.000 1.0460 0.01798 0.00990 -0.1471 0.6970 1.0000
4.250 1.0733 0.01799 0.00990 -0.1467 0.6840 1.0000
4.500 1.1006 0.01801 0.00992 -0.1463 0.6700 1.0000
4.750 1.1265 0.01807 0.00997 -0.1456 0.6543 1.0000
5.000 1.1511 0.01817 0.01008 -0.1447 0.6370 1.0000
5.250 1.1752 0.01829 0.01019 -0.1437 0.6179 1.0000
5.500 1.2000 0.01843 0.01028 -0.1429 0.5974 1.0000
5.750 1.2217 0.01867 0.01051 -0.1415 0.5748 1.0000
6.000 1.2431 0.01895 0.01071 -0.1401 0.5500 1.0000
6.250 1.2616 0.01932 0.01102 -0.1382 0.5234 1.0000
6.500 1.2792 0.01976 0.01136 -0.1362 0.4959 1.0000
6.750 1.2953 0.02029 0.01179 -0.1340 0.4674 1.0000
7.000 1.3096 0.02090 0.01230 -0.1315 0.4385 1.0000
7.250 1.3225 0.02159 0.01288 -0.1290 0.4094 1.0000
7.500 1.3343 0.02237 0.01355 -0.1263 0.3804 1.0000
7.750 1.3451 0.02322 0.01431 -0.1236 0.3530 1.0000
8.000 1.3548 0.02416 0.01513 -0.1208 0.3263 1.0000
8.250 1.3646 0.02514 0.01603 -0.1182 0.3004 1.0000
8.500 1.3736 0.02620 0.01700 -0.1156 0.2768 1.0000
8.750 1.3825 0.02731 0.01806 -0.1130 0.2540 1.0000
9.000 1.3905 0.02852 0.01919 -0.1105 0.2338 1.0000
9.250 1.3995 0.02972 0.02035 -0.1082 0.2148 1.0000
9.500 1.4081 0.03099 0.02159 -0.1059 0.1977 1.0000
9.750 1.4166 0.03230 0.02290 -0.1037 0.1827 1.0000
10.000 1.4247 0.03368 0.02429 -0.1016 0.1693 1.0000
10.250 1.4323 0.03514 0.02575 -0.0996 0.1578 1.0000
10.500 1.4403 0.03662 0.02726 -0.0976 0.1471 1.0000
10.750 1.4487 0.03811 0.02882 -0.0958 0.1375 1.0000
11.000 1.4551 0.03979 0.03052 -0.0939 0.1296 1.0000
11.250 1.4631 0.04140 0.03223 -0.0923 0.1216 1.0000
11.500 1.4692 0.04319 0.03406 -0.0906 0.1151 1.0000
11.750 1.4761 0.04496 0.03594 -0.0890 0.1084 1.0000
12.000 1.4810 0.04697 0.03797 -0.0874 0.1031 1.0000
12.500 1.4914 0.05103 0.04224 -0.0847 0.0928 1.0000
12.750 1.4977 0.05307 0.04443 -0.0834 0.0880 1.0000
13.000 1.5025 0.05527 0.04676 -0.0823 0.0838 1.0000
13.250 1.5045 0.05777 0.04927 -0.0811 0.0804 1.0000
13.500 1.5100 0.06005 0.05177 -0.0802 0.0764 1.0000
13.750 1.5135 0.06255 0.05442 -0.0793 0.0729 1.0000
14.000 1.5151 0.06527 0.05721 -0.0786 0.0701 1.0000
14.250 1.5178 0.06801 0.06009 -0.0779 0.0672 1.0000
14.500 1.5201 0.07085 0.06315 -0.0774 0.0642 1.0000
14.750 1.5210 0.07387 0.06631 -0.0771 0.0617 1.0000
15.000 1.5208 0.07705 0.06956 -0.0769 0.0596 1.0000
15.250 1.5210 0.08035 0.07304 -0.0768 0.0574 1.0000
15.500 1.5200 0.08391 0.07686 -0.0769 0.0552 1.0000
15.750 1.5183 0.08759 0.08071 -0.0772 0.0532 1.0000
16.000 1.5161 0.09132 0.08457 -0.0778 0.0516 1.0000
16.250 1.5147 0.09497 0.08827 -0.0784 0.0501 1.0000
16.500 1.5099 0.09940 0.09296 -0.0794 0.0486 1.0000
16.750 1.5033 0.10425 0.09808 -0.0808 0.0471 1.0000
17.000 1.4966 0.10918 0.10324 -0.0824 0.0458 1.0000
17.250 1.4902 0.11413 0.10837 -0.0844 0.0447 1.0000
17.500 1.4844 0.11900 0.11339 -0.0865 0.0436 1.0000
17.750 1.4809 0.12344 0.11791 -0.0885 0.0425 1.0000
18.000 1.4767 0.12808 0.12263 -0.0906 0.0416 1.0000
18.250 1.4607 0.13555 0.13041 -0.0949 0.0410 1.0000
18.500 1.4424 0.14383 0.13897 -0.1000 0.0405 1.0000
18.750 1.4207 0.15336 0.14877 -0.1064 0.0401 1.0000
19.000 1.3915 0.16540 0.16106 -0.1148 0.0400 1.0000
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