SG6050 (sg6050-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 200,000 Max Cl/Cd: 73.22 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6050-il-200000-n5.txt Download as CSV file: xf-sg6050-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6050
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6279 0.12971 0.12574 -0.0292 1.0000 0.0148
-15.750 -0.6590 0.11849 0.11439 -0.0345 1.0000 0.0147
-15.500 -0.6875 0.10827 0.10403 -0.0396 1.0000 0.0146
-15.250 -0.7168 0.09816 0.09378 -0.0448 1.0000 0.0145
-15.000 -0.7448 0.08875 0.08421 -0.0499 1.0000 0.0144
-14.750 -0.7703 0.08043 0.07573 -0.0546 1.0000 0.0143
-14.500 -0.7928 0.07294 0.06810 -0.0589 1.0000 0.0143
-14.250 -0.8122 0.06623 0.06125 -0.0629 1.0000 0.0142
-14.000 -0.8288 0.06008 0.05497 -0.0667 1.0000 0.0143
-13.750 -0.8423 0.05438 0.04913 -0.0704 1.0000 0.0144
-13.500 -0.8527 0.04910 0.04369 -0.0741 1.0000 0.0145
-13.250 -0.8604 0.04438 0.03882 -0.0775 1.0000 0.0147
-13.000 -0.8665 0.04041 0.03470 -0.0801 1.0000 0.0149
-12.750 -0.8723 0.03732 0.03148 -0.0811 1.0000 0.0152
-12.500 -0.8791 0.03503 0.02907 -0.0801 1.0000 0.0155
-12.250 -0.8906 0.03347 0.02741 -0.0768 1.0000 0.0157
-12.000 -0.8894 0.03196 0.02577 -0.0750 0.9959 0.0163
-11.750 -0.8703 0.03012 0.02379 -0.0765 0.9857 0.0173
-11.500 -0.8500 0.02856 0.02210 -0.0775 0.9741 0.0188
-11.250 -0.8288 0.02713 0.02054 -0.0783 0.9625 0.0207
-11.000 -0.8065 0.02584 0.01913 -0.0789 0.9519 0.0233
-10.750 -0.7828 0.02469 0.01791 -0.0795 0.9422 0.0268
-10.500 -0.7597 0.02381 0.01697 -0.0796 0.9315 0.0311
-10.250 -0.7351 0.02312 0.01620 -0.0798 0.9223 0.0360
-10.000 -0.7106 0.02255 0.01551 -0.0798 0.9130 0.0408
-9.750 -0.6858 0.02210 0.01493 -0.0796 0.9041 0.0454
-9.500 -0.6615 0.02166 0.01440 -0.0795 0.8956 0.0493
-9.250 -0.6365 0.02130 0.01390 -0.0793 0.8875 0.0535
-9.000 -0.6121 0.02090 0.01343 -0.0791 0.8799 0.0578
-8.750 -0.5862 0.02069 0.01308 -0.0791 0.8730 0.0630
-8.500 -0.5619 0.02025 0.01258 -0.0789 0.8656 0.0673
-8.250 -0.5369 0.01988 0.01212 -0.0786 0.8597 0.0711
-8.000 -0.5112 0.01948 0.01158 -0.0786 0.8527 0.0743
-7.750 -0.4865 0.01893 0.01095 -0.0783 0.8466 0.0772
-7.500 -0.4614 0.01845 0.01042 -0.0781 0.8411 0.0803
-7.250 -0.4354 0.01803 0.00992 -0.0781 0.8346 0.0835
-7.000 -0.4091 0.01767 0.00943 -0.0780 0.8292 0.0867
-6.750 -0.3833 0.01719 0.00891 -0.0779 0.8239 0.0901
-6.500 -0.3568 0.01677 0.00846 -0.0779 0.8179 0.0939
-6.250 -0.3299 0.01644 0.00803 -0.0780 0.8128 0.0985
-6.000 -0.3030 0.01608 0.00761 -0.0780 0.8081 0.1038
-5.750 -0.2758 0.01572 0.00724 -0.0782 0.8024 0.1106
-5.500 -0.2484 0.01539 0.00687 -0.0783 0.7973 0.1189
-5.000 -0.1935 0.01466 0.00619 -0.0787 0.7875 0.1529
-4.750 -0.1663 0.01421 0.00587 -0.0790 0.7823 0.1889
-4.500 -0.1392 0.01376 0.00562 -0.0792 0.7779 0.2440
-4.250 -0.1112 0.01354 0.00554 -0.0795 0.7731 0.2912
-4.000 -0.0826 0.01345 0.00549 -0.0798 0.7678 0.3230
-3.750 -0.0537 0.01341 0.00540 -0.0800 0.7630 0.3449
-3.500 -0.0248 0.01338 0.00531 -0.0803 0.7587 0.3605
-3.250 0.0042 0.01335 0.00525 -0.0806 0.7530 0.3731
-3.000 0.0332 0.01332 0.00516 -0.0808 0.7478 0.3849
-2.750 0.0622 0.01328 0.00504 -0.0811 0.7435 0.3959
-2.500 0.0910 0.01323 0.00502 -0.0814 0.7375 0.4091
-2.250 0.1196 0.01319 0.00498 -0.0816 0.7321 0.4276
-2.000 0.1483 0.01312 0.00491 -0.0818 0.7277 0.4425
-1.750 0.1774 0.01308 0.00484 -0.0822 0.7220 0.4498
-1.500 0.2062 0.01299 0.00477 -0.0824 0.7165 0.4557
-1.250 0.2352 0.01294 0.00467 -0.0827 0.7117 0.4625
-1.000 0.2641 0.01288 0.00463 -0.0830 0.7061 0.4694
-0.750 0.2929 0.01282 0.00460 -0.0833 0.7002 0.4769
-0.500 0.3218 0.01277 0.00452 -0.0835 0.6952 0.4854
-0.250 0.3505 0.01272 0.00453 -0.0838 0.6891 0.4952
0.000 0.3792 0.01266 0.00451 -0.0841 0.6829 0.5063
0.250 0.4079 0.01260 0.00446 -0.0843 0.6777 0.5205
0.500 0.4362 0.01254 0.00452 -0.0845 0.6705 0.5385
0.750 0.4644 0.01245 0.00451 -0.0846 0.6644 0.5626
1.000 0.4922 0.01235 0.00456 -0.0847 0.6579 0.5980
1.250 0.5192 0.01222 0.00463 -0.0845 0.6511 0.6487
1.500 0.5448 0.01205 0.00467 -0.0839 0.6452 0.7141
1.750 0.5667 0.01192 0.00485 -0.0822 0.6378 0.7938
2.000 0.5891 0.01188 0.00492 -0.0806 0.6314 0.8696
2.250 0.6150 0.01191 0.00499 -0.0799 0.6240 0.9119
2.500 0.6449 0.01194 0.00502 -0.0802 0.6166 0.9434
2.750 0.6782 0.01200 0.00508 -0.0814 0.6085 0.9694
3.000 0.7134 0.01207 0.00512 -0.0831 0.6001 0.9910
3.250 0.7434 0.01214 0.00518 -0.0837 0.5914 1.0000
3.500 0.7699 0.01226 0.00525 -0.0836 0.5832 1.0000
3.750 0.7963 0.01240 0.00539 -0.0835 0.5742 1.0000
4.000 0.8229 0.01254 0.00548 -0.0834 0.5659 1.0000
4.250 0.8494 0.01269 0.00564 -0.0833 0.5563 1.0000
4.500 0.8758 0.01286 0.00579 -0.0832 0.5473 1.0000
4.750 0.9021 0.01304 0.00596 -0.0831 0.5375 1.0000
5.000 0.9282 0.01323 0.00615 -0.0829 0.5277 1.0000
5.250 0.9541 0.01345 0.00633 -0.0827 0.5177 1.0000
5.500 0.9795 0.01367 0.00655 -0.0825 0.5061 1.0000
5.750 1.0047 0.01390 0.00679 -0.0821 0.4944 1.0000
6.000 1.0294 0.01417 0.00703 -0.0818 0.4828 1.0000
6.250 1.0537 0.01445 0.00729 -0.0813 0.4708 1.0000
6.500 1.0778 0.01473 0.00759 -0.0808 0.4583 1.0000
6.750 1.1012 0.01504 0.00791 -0.0802 0.4455 1.0000
7.000 1.1239 0.01539 0.00824 -0.0795 0.4323 1.0000
7.250 1.1458 0.01576 0.00860 -0.0787 0.4191 1.0000
7.500 1.1670 0.01616 0.00898 -0.0778 0.4057 1.0000
7.750 1.1874 0.01657 0.00940 -0.0767 0.3918 1.0000
8.000 1.2068 0.01702 0.00984 -0.0755 0.3771 1.0000
8.250 1.2247 0.01751 0.01033 -0.0741 0.3616 1.0000
8.500 1.2410 0.01804 0.01085 -0.0724 0.3459 1.0000
8.750 1.2556 0.01862 0.01142 -0.0705 0.3304 1.0000
9.000 1.2669 0.01924 0.01203 -0.0680 0.3152 1.0000
9.250 1.2773 0.01996 0.01274 -0.0654 0.2996 1.0000
9.500 1.2871 0.02078 0.01355 -0.0630 0.2834 1.0000
9.750 1.2954 0.02176 0.01448 -0.0606 0.2661 1.0000
10.000 1.3036 0.02283 0.01552 -0.0584 0.2476 1.0000
10.250 1.3107 0.02403 0.01669 -0.0562 0.2286 1.0000
10.500 1.3169 0.02538 0.01800 -0.0542 0.2104 1.0000
10.750 1.3227 0.02685 0.01943 -0.0522 0.1935 1.0000
11.000 1.3279 0.02842 0.02096 -0.0504 0.1778 1.0000
11.250 1.3327 0.03009 0.02261 -0.0487 0.1629 1.0000
11.500 1.3368 0.03189 0.02438 -0.0471 0.1484 1.0000
11.750 1.3399 0.03381 0.02627 -0.0456 0.1340 1.0000
12.000 1.3425 0.03585 0.02829 -0.0442 0.1201 1.0000
12.250 1.3441 0.03801 0.03041 -0.0428 0.1072 1.0000
12.500 1.3455 0.04025 0.03263 -0.0416 0.0953 1.0000
12.750 1.3474 0.04250 0.03488 -0.0405 0.0847 1.0000
13.000 1.3492 0.04480 0.03720 -0.0395 0.0760 1.0000
13.250 1.3507 0.04721 0.03963 -0.0386 0.0689 1.0000
13.500 1.3516 0.04975 0.04221 -0.0379 0.0625 1.0000
13.750 1.3535 0.05227 0.04478 -0.0372 0.0568 1.0000
14.000 1.3530 0.05511 0.04766 -0.0367 0.0519 1.0000
14.250 1.3545 0.05781 0.05044 -0.0363 0.0472 1.0000
14.500 1.3535 0.06086 0.05354 -0.0360 0.0434 1.0000
14.750 1.3538 0.06384 0.05661 -0.0359 0.0397 1.0000
15.000 1.3515 0.06719 0.06001 -0.0358 0.0367 1.0000
15.250 1.3508 0.07041 0.06333 -0.0359 0.0338 1.0000
15.500 1.3472 0.07409 0.06708 -0.0361 0.0314 1.0000
15.750 1.3452 0.07762 0.07071 -0.0364 0.0290 1.0000
16.000 1.3412 0.08148 0.07467 -0.0368 0.0270 1.0000
16.250 1.3361 0.08554 0.07881 -0.0375 0.0254 1.0000
16.500 1.3324 0.08950 0.08289 -0.0381 0.0238 1.0000
16.750 1.3268 0.09379 0.08727 -0.0390 0.0224 1.0000
17.000 1.3197 0.09839 0.09194 -0.0402 0.0215 1.0000
17.250 1.3152 0.10263 0.09632 -0.0412 0.0203 1.0000
17.500 1.3097 0.10709 0.10090 -0.0425 0.0194 1.0000
17.750 1.3034 0.11176 0.10567 -0.0440 0.0187 1.0000
18.000 1.2959 0.11667 0.11068 -0.0457 0.0181 1.0000
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