GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 A AIRFOIL (goe802a-il) Reynolds number: 200,000 Max Cl/Cd: 73.91 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802a-il-200000.txt Download as CSV file: xf-goe802a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3050 0.09445 0.09101 -0.0264 1.0000 0.0371
-8.000 -0.3030 0.09188 0.08849 -0.0276 1.0000 0.0380
-7.750 -0.3111 0.09026 0.08696 -0.0272 1.0000 0.0387
-7.500 -0.2836 0.08314 0.08020 -0.0278 0.9954 0.0396
-7.250 -0.2638 0.07807 0.07513 -0.0282 0.9935 0.0402
-7.000 -0.2479 0.07367 0.07072 -0.0320 0.9878 0.0410
-6.750 -0.3204 0.08090 0.07775 -0.0316 0.9944 0.0399
-6.500 -0.2973 0.07678 0.07362 -0.0352 0.9901 0.0407
-6.250 -0.2685 0.07261 0.06940 -0.0413 0.9848 0.0418
-6.000 -0.2322 0.06804 0.06475 -0.0495 0.9809 0.0437
-5.750 -0.1847 0.06322 0.05962 -0.0621 0.9720 0.0457
-5.500 -0.1599 0.05897 0.05543 -0.0644 0.9687 0.0464
-5.250 -0.1254 0.05527 0.05166 -0.0694 0.9655 0.0480
-5.000 -0.0761 0.05273 0.04858 -0.0775 0.9567 0.0519
-4.750 -0.0496 0.04812 0.04411 -0.0800 0.9527 0.0524
-4.500 -0.0216 0.04505 0.04100 -0.0824 0.9458 0.0536
-4.250 0.0095 0.04237 0.03818 -0.0847 0.9374 0.0559
-4.000 0.0466 0.04032 0.03569 -0.0870 0.9286 0.0584
-3.750 0.0685 0.03733 0.03272 -0.0874 0.9187 0.0593
-3.500 0.0921 0.03529 0.03057 -0.0874 0.9079 0.0613
-3.250 0.1229 0.03432 0.02916 -0.0872 0.8985 0.0645
-3.000 0.1425 0.03167 0.02655 -0.0868 0.8867 0.0658
-2.750 0.1685 0.03049 0.02511 -0.0861 0.8765 0.0692
-2.500 0.1939 0.02910 0.02346 -0.0853 0.8644 0.0702
-2.250 0.2172 0.02718 0.02146 -0.0848 0.8520 0.0717
-2.000 0.2438 0.02637 0.02037 -0.0839 0.8408 0.0741
-1.750 0.2715 0.02615 0.01976 -0.0829 0.8277 0.0749
-1.500 0.2956 0.02376 0.01736 -0.0826 0.8144 0.0757
-1.250 0.3218 0.02254 0.01596 -0.0820 0.8013 0.0771
-1.000 0.3494 0.02231 0.01541 -0.0811 0.7875 0.0790
-0.750 0.3766 0.02175 0.01458 -0.0804 0.7723 0.0796
-0.500 0.4027 0.02020 0.01293 -0.0800 0.7559 0.0803
-0.250 0.4295 0.01933 0.01190 -0.0795 0.7392 0.0810
0.000 0.3916 0.00804 0.00188 -0.0689 0.7176 0.0740
0.250 0.4839 0.01813 0.01032 -0.0784 0.7048 0.0815
0.500 0.5111 0.01765 0.00965 -0.0779 0.6872 0.0812
0.750 0.5384 0.01728 0.00909 -0.0773 0.6697 0.0805
1.000 0.5660 0.01753 0.00907 -0.0767 0.6527 0.0793
1.250 0.5930 0.01705 0.00846 -0.0763 0.6364 0.0793
1.500 0.6199 0.01675 0.00802 -0.0759 0.6205 0.0838
1.750 0.6469 0.01652 0.00765 -0.0755 0.6052 0.0839
2.000 0.6736 0.01615 0.00716 -0.0751 0.5905 0.0884
2.250 0.6999 0.01535 0.00633 -0.0748 0.5760 0.1000
2.500 0.7244 0.01377 0.00508 -0.0745 0.5621 0.1276
2.750 0.7501 0.01319 0.00469 -0.0742 0.5482 0.2117
3.000 0.7782 0.01170 0.00483 -0.0742 0.5329 1.0000
3.250 0.8040 0.01196 0.00493 -0.0738 0.5181 1.0000
3.500 0.8299 0.01222 0.00504 -0.0734 0.5044 1.0000
3.750 0.8559 0.01244 0.00522 -0.0730 0.4906 1.0000
4.000 0.8818 0.01269 0.00540 -0.0727 0.4784 1.0000
4.250 0.9077 0.01299 0.00557 -0.0724 0.4680 1.0000
4.500 0.9337 0.01321 0.00579 -0.0721 0.4566 1.0000
4.750 0.9595 0.01350 0.00602 -0.0718 0.4465 1.0000
5.000 0.9853 0.01374 0.00623 -0.0715 0.4359 1.0000
5.250 1.0110 0.01402 0.00649 -0.0712 0.4261 1.0000
5.500 1.0365 0.01431 0.00674 -0.0709 0.4168 1.0000
5.750 1.0618 0.01457 0.00702 -0.0705 0.4063 1.0000
6.000 1.0868 0.01489 0.00725 -0.0701 0.3962 1.0000
6.250 1.1115 0.01512 0.00753 -0.0697 0.3844 1.0000
6.500 1.1359 0.01541 0.00783 -0.0692 0.3728 1.0000
6.750 1.1598 0.01575 0.00809 -0.0687 0.3609 1.0000
7.000 1.1834 0.01602 0.00839 -0.0681 0.3475 1.0000
7.250 1.2070 0.01633 0.00873 -0.0675 0.3343 1.0000
7.500 1.2300 0.01669 0.00910 -0.0669 0.3215 1.0000
7.750 1.2522 0.01709 0.00947 -0.0661 0.3075 1.0000
8.000 1.2739 0.01751 0.00987 -0.0653 0.2925 1.0000
8.250 1.2951 0.01794 0.01032 -0.0644 0.2761 1.0000
8.500 1.3155 0.01841 0.01080 -0.0634 0.2578 1.0000
8.750 1.3351 0.01894 0.01130 -0.0624 0.2391 1.0000
9.000 1.3538 0.01954 0.01186 -0.0613 0.2214 1.0000
9.250 1.3713 0.02024 0.01250 -0.0600 0.2065 1.0000
9.750 1.4041 0.02176 0.01399 -0.0572 0.1821 1.0000
10.000 1.4194 0.02257 0.01480 -0.0557 0.1720 1.0000
10.250 1.4315 0.02352 0.01571 -0.0538 0.1630 1.0000
10.500 1.4457 0.02424 0.01653 -0.0521 0.1545 1.0000
10.750 1.4539 0.02527 0.01753 -0.0496 0.1471 1.0000
11.000 1.4671 0.02605 0.01844 -0.0480 0.1396 1.0000
11.250 1.4761 0.02711 0.01951 -0.0460 0.1331 1.0000
11.500 1.4867 0.02814 0.02063 -0.0443 0.1272 1.0000
11.750 1.4975 0.02916 0.02175 -0.0428 0.1212 1.0000
12.000 1.5039 0.03054 0.02313 -0.0411 0.1154 1.0000
12.250 1.5166 0.03151 0.02428 -0.0400 0.1091 1.0000
12.500 1.5233 0.03298 0.02577 -0.0387 0.1033 1.0000
12.750 1.5332 0.03427 0.02719 -0.0376 0.0973 1.0000
13.000 1.5401 0.03586 0.02885 -0.0366 0.0909 1.0000
13.250 1.5467 0.03757 0.03065 -0.0357 0.0837 1.0000
13.500 1.5485 0.03980 0.03291 -0.0349 0.0769 1.0000
13.750 1.5503 0.04214 0.03532 -0.0342 0.0694 1.0000
14.000 1.5470 0.04513 0.03836 -0.0336 0.0629 1.0000
14.250 1.5421 0.04843 0.04172 -0.0333 0.0561 1.0000
14.500 1.5368 0.05192 0.04532 -0.0332 0.0493 1.0000
14.750 1.5277 0.05602 0.04948 -0.0335 0.0440 1.0000
15.000 1.5199 0.06011 0.05366 -0.0340 0.0387 1.0000
15.250 1.5093 0.06474 0.05836 -0.0348 0.0358 1.0000
15.500 1.4986 0.06953 0.06327 -0.0359 0.0336 1.0000
15.750 1.4865 0.07468 0.06852 -0.0372 0.0321 1.0000
16.000 1.4727 0.08020 0.07415 -0.0388 0.0310 1.0000
16.250 1.4582 0.08597 0.08003 -0.0406 0.0303 1.0000
16.500 1.4452 0.09164 0.08583 -0.0424 0.0297 1.0000
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