SG6041 (sg6041-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 200,000 Max Cl/Cd: 72.82 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6041-il-200000.txt Download as CSV file: xf-sg6041-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SG6041
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4366 0.08647 0.08299 -0.0397 1.0000 0.0472
-8.500 -0.4530 0.08219 0.07881 -0.0429 1.0000 0.0480
-8.250 -0.4712 0.07888 0.07557 -0.0434 1.0000 0.0480
-8.000 -0.4926 0.07647 0.07320 -0.0413 1.0000 0.0479
-7.750 -0.5155 0.07363 0.07033 -0.0399 1.0000 0.0483
-7.500 -0.5407 0.07119 0.06771 -0.0380 1.0000 0.0488
-7.250 -0.5524 0.06896 0.06531 -0.0357 1.0000 0.0490
-7.000 -0.5593 0.06641 0.06257 -0.0336 1.0000 0.0492
-6.750 -0.5627 0.05948 0.05581 -0.0327 1.0000 0.0504
-6.500 -0.5589 0.05682 0.05317 -0.0309 1.0000 0.0512
-6.250 -0.5543 0.05445 0.05077 -0.0292 1.0000 0.0525
-6.000 -0.5489 0.05190 0.04813 -0.0277 1.0000 0.0544
-5.750 -0.5336 0.04852 0.04449 -0.0283 0.9985 0.0579
-5.500 -0.5075 0.04325 0.03866 -0.0316 0.9943 0.0633
-5.250 -0.4821 0.04096 0.03641 -0.0329 0.9907 0.0679
-5.000 -0.4534 0.03062 0.02463 -0.0323 0.9873 0.0407
-4.750 -0.4217 0.02624 0.01965 -0.0327 0.9851 0.0339
-4.500 -0.3899 0.02302 0.01576 -0.0328 0.9827 0.0321
-4.250 -0.3599 0.02139 0.01388 -0.0331 0.9789 0.0324
-4.000 -0.3267 0.02017 0.01252 -0.0340 0.9754 0.0345
-3.750 -0.2894 0.01953 0.01169 -0.0358 0.9724 0.0389
-3.500 -0.2600 0.01818 0.01040 -0.0363 0.9686 0.0434
-3.250 -0.2299 0.01726 0.00944 -0.0367 0.9637 0.0514
-3.000 -0.1948 0.01652 0.00877 -0.0383 0.9600 0.0690
-2.750 -0.1582 0.01585 0.00819 -0.0403 0.9569 0.1028
-2.500 -0.1341 0.01507 0.00773 -0.0400 0.9501 0.1565
-2.250 -0.1127 0.01295 0.00762 -0.0397 0.9458 0.6014
-2.000 -0.0864 0.01278 0.00787 -0.0385 0.9409 0.7528
-1.750 -0.0620 0.01276 0.00791 -0.0370 0.9339 0.8067
-1.500 -0.0273 0.01274 0.00790 -0.0375 0.9301 0.8466
-1.250 -0.0041 0.01274 0.00790 -0.0359 0.9227 0.8769
-1.000 0.0296 0.01270 0.00784 -0.0362 0.9178 0.9049
-0.750 0.0749 0.01271 0.00779 -0.0388 0.9154 0.9331
-0.500 0.1468 0.01297 0.00798 -0.0463 0.9161 0.9637
-0.250 0.2103 0.01288 0.00780 -0.0532 0.9152 0.9712
0.000 0.2647 0.01267 0.00753 -0.0584 0.9114 0.9745
0.250 0.3124 0.01242 0.00724 -0.0624 0.9052 0.9790
0.500 0.3627 0.01203 0.00681 -0.0666 0.9010 0.9820
0.750 0.4068 0.01172 0.00649 -0.0698 0.8929 0.9863
1.000 0.4537 0.01129 0.00604 -0.0733 0.8860 0.9894
1.250 0.4938 0.01098 0.00573 -0.0756 0.8749 0.9948
1.500 0.5359 0.01063 0.00538 -0.0783 0.8636 0.9995
1.750 0.5584 0.01038 0.00512 -0.0771 0.8496 1.0000
2.000 0.5772 0.01018 0.00491 -0.0752 0.8345 1.0000
2.250 0.5949 0.01001 0.00473 -0.0730 0.8178 1.0000
2.500 0.6125 0.00986 0.00456 -0.0708 0.7998 1.0000
2.750 0.6318 0.00972 0.00437 -0.0688 0.7807 1.0000
3.000 0.6480 0.00967 0.00430 -0.0664 0.7577 1.0000
3.250 0.6677 0.00964 0.00420 -0.0644 0.7330 1.0000
3.500 0.6877 0.00967 0.00415 -0.0626 0.7039 1.0000
3.750 0.7074 0.00978 0.00414 -0.0607 0.6696 1.0000
4.000 0.7267 0.00998 0.00417 -0.0587 0.6292 1.0000
4.250 0.7448 0.01029 0.00426 -0.0565 0.5826 1.0000
4.500 0.7619 0.01069 0.00444 -0.0543 0.5323 1.0000
4.750 0.7783 0.01117 0.00466 -0.0520 0.4794 1.0000
5.000 0.7944 0.01172 0.00494 -0.0498 0.4274 1.0000
5.250 0.8108 0.01230 0.00528 -0.0477 0.3771 1.0000
5.500 0.8277 0.01291 0.00567 -0.0458 0.3309 1.0000
5.750 0.8448 0.01355 0.00610 -0.0440 0.2892 1.0000
6.000 0.8626 0.01420 0.00655 -0.0424 0.2527 1.0000
6.250 0.8810 0.01485 0.00705 -0.0409 0.2231 1.0000
6.500 0.8998 0.01551 0.00761 -0.0395 0.1988 1.0000
6.750 0.9184 0.01619 0.00817 -0.0381 0.1785 1.0000
7.000 0.9368 0.01693 0.00880 -0.0366 0.1612 1.0000
7.250 0.9559 0.01763 0.00945 -0.0353 0.1464 1.0000
7.500 0.9747 0.01838 0.01016 -0.0340 0.1338 1.0000
7.750 0.9948 0.01897 0.01078 -0.0328 0.1225 1.0000
8.000 1.0142 0.01970 0.01154 -0.0315 0.1128 1.0000
8.250 1.0326 0.02058 0.01238 -0.0302 0.1046 1.0000
8.500 1.0520 0.02120 0.01308 -0.0290 0.0969 1.0000
8.750 1.0705 0.02216 0.01406 -0.0277 0.0900 1.0000
9.000 1.0888 0.02288 0.01483 -0.0264 0.0835 1.0000
9.250 1.1075 0.02405 0.01604 -0.0252 0.0778 1.0000
9.500 1.1247 0.02478 0.01686 -0.0237 0.0721 1.0000
9.750 1.1432 0.02623 0.01831 -0.0228 0.0670 1.0000
10.000 1.1597 0.02715 0.01942 -0.0211 0.0627 1.0000
10.250 1.1756 0.02817 0.02046 -0.0196 0.0590 1.0000
10.500 1.1948 0.03006 0.02245 -0.0189 0.0553 1.0000
10.750 1.2079 0.03116 0.02377 -0.0168 0.0524 1.0000
11.000 1.2215 0.03240 0.02515 -0.0151 0.0499 1.0000
11.250 1.2358 0.03380 0.02658 -0.0137 0.0476 1.0000
11.500 1.2495 0.03658 0.02958 -0.0126 0.0454 1.0000
11.750 1.2545 0.03795 0.03122 -0.0098 0.0439 1.0000
12.000 1.2592 0.03974 0.03327 -0.0072 0.0424 1.0000
12.250 1.2628 0.04165 0.03539 -0.0048 0.0411 1.0000
12.500 1.2647 0.04348 0.03740 -0.0025 0.0398 1.0000
12.750 1.2684 0.04510 0.03909 -0.0007 0.0385 1.0000
13.000 1.2700 0.04794 0.04202 0.0009 0.0372 1.0000
13.250 1.2558 0.05231 0.04669 0.0031 0.0365 1.0000
13.500 1.2427 0.05500 0.04967 0.0051 0.0361 1.0000
13.750 1.2272 0.05851 0.05345 0.0064 0.0358 1.0000
14.000 1.2090 0.06276 0.05797 0.0069 0.0356 1.0000
14.250 1.1886 0.06762 0.06307 0.0064 0.0355 1.0000
14.500 1.1653 0.07337 0.06906 0.0047 0.0355 1.0000
14.750 1.1400 0.08006 0.07597 0.0019 0.0356 1.0000
15.000 1.1114 0.08803 0.08415 -0.0025 0.0358 1.0000
15.250 1.0805 0.09746 0.09374 -0.0083 0.0361 1.0000
15.500 1.0461 0.10880 0.10522 -0.0153 0.0366 1.0000
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Polar data table (+)
Polar graphs
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