GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 200,000 Max Cl/Cd: 66.22 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe633-il-200000-n5.txt Download as CSV file: xf-goe633-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6120 0.05314 0.04891 -0.0679 1.0000 0.0344
-11.000 -0.6353 0.04511 0.04034 -0.0764 0.8905 0.0343
-10.750 -0.6469 0.04171 0.03644 -0.0756 0.8473 0.0344
-10.500 -0.6521 0.03918 0.03352 -0.0736 0.8270 0.0345
-10.250 -0.6522 0.03699 0.03095 -0.0713 0.8127 0.0346
-10.000 -0.6482 0.03514 0.02870 -0.0691 0.8011 0.0348
-9.750 -0.6387 0.03340 0.02670 -0.0672 0.7915 0.0351
-9.500 -0.6244 0.03193 0.02508 -0.0658 0.7831 0.0355
-9.250 -0.6087 0.03064 0.02364 -0.0645 0.7751 0.0358
-9.000 -0.5922 0.02944 0.02226 -0.0631 0.7675 0.0361
-8.750 -0.5746 0.02829 0.02092 -0.0618 0.7606 0.0364
-8.500 -0.5559 0.02718 0.01964 -0.0605 0.7536 0.0367
-8.250 -0.5364 0.02617 0.01844 -0.0593 0.7477 0.0370
-8.000 -0.5158 0.02521 0.01732 -0.0582 0.7414 0.0373
-7.750 -0.4945 0.02431 0.01627 -0.0571 0.7350 0.0376
-7.500 -0.4726 0.02350 0.01530 -0.0561 0.7295 0.0380
-7.250 -0.4499 0.02270 0.01439 -0.0552 0.7236 0.0384
-7.000 -0.4268 0.02197 0.01354 -0.0543 0.7179 0.0388
-6.750 -0.4035 0.02130 0.01274 -0.0534 0.7128 0.0392
-6.500 -0.3796 0.02072 0.01205 -0.0526 0.7074 0.0398
-6.250 -0.3552 0.02020 0.01141 -0.0518 0.7015 0.0404
-6.000 -0.3320 0.01947 0.01067 -0.0510 0.6963 0.0410
-5.750 -0.3083 0.01891 0.01007 -0.0501 0.6920 0.0417
-5.500 -0.2839 0.01839 0.00955 -0.0494 0.6864 0.0423
-5.250 -0.2594 0.01794 0.00905 -0.0487 0.6809 0.0429
-5.000 -0.2348 0.01753 0.00856 -0.0479 0.6762 0.0437
-4.750 -0.2097 0.01714 0.00812 -0.0472 0.6713 0.0445
-4.500 -0.1843 0.01679 0.00773 -0.0466 0.6660 0.0454
-4.250 -0.1587 0.01649 0.00734 -0.0459 0.6610 0.0462
-4.000 -0.1334 0.01613 0.00691 -0.0452 0.6566 0.0474
-3.750 -0.1076 0.01579 0.00656 -0.0447 0.6499 0.0493
-3.500 -0.0816 0.01550 0.00621 -0.0441 0.6431 0.0517
-3.250 -0.0557 0.01519 0.00584 -0.0435 0.6359 0.0550
-3.000 -0.0297 0.01486 0.00552 -0.0429 0.6277 0.0605
-2.750 -0.0042 0.01442 0.00521 -0.0423 0.6218 0.0863
-2.500 0.0220 0.01413 0.00504 -0.0419 0.6155 0.1191
-2.250 0.0483 0.01392 0.00494 -0.0414 0.6095 0.1441
-2.000 0.0749 0.01381 0.00486 -0.0410 0.6043 0.1685
-1.750 0.1019 0.01376 0.00483 -0.0406 0.5983 0.1869
-1.500 0.1288 0.01371 0.00478 -0.0402 0.5922 0.2008
-1.250 0.1554 0.01366 0.00468 -0.0397 0.5868 0.2119
-1.000 0.1824 0.01363 0.00464 -0.0393 0.5801 0.2229
-0.750 0.2088 0.01356 0.00460 -0.0389 0.5737 0.2357
-0.500 0.2352 0.01352 0.00454 -0.0384 0.5683 0.2484
-0.250 0.2620 0.01349 0.00453 -0.0380 0.5615 0.2602
0.000 0.2880 0.01341 0.00446 -0.0375 0.5550 0.2691
0.250 0.3144 0.01337 0.00440 -0.0370 0.5483 0.2769
0.500 0.3403 0.01330 0.00436 -0.0364 0.5407 0.2846
0.750 0.3662 0.01327 0.00429 -0.0358 0.5341 0.2950
1.000 0.3919 0.01320 0.00431 -0.0353 0.5264 0.3073
1.250 0.4173 0.01315 0.00428 -0.0346 0.5192 0.3228
1.500 0.4422 0.01307 0.00429 -0.0339 0.5115 0.3471
1.750 0.4659 0.01291 0.00430 -0.0330 0.5034 0.3904
2.000 0.4842 0.01238 0.00431 -0.0311 0.4954 0.5466
2.250 0.5864 0.01213 0.00492 -0.0453 0.4805 0.9506
2.500 0.6260 0.01235 0.00507 -0.0475 0.4697 0.9663
2.750 0.6729 0.01254 0.00519 -0.0512 0.4581 0.9783
3.000 0.7204 0.01269 0.00524 -0.0553 0.4453 0.9877
3.250 0.7627 0.01285 0.00528 -0.0583 0.4306 0.9946
3.500 0.8041 0.01298 0.00531 -0.0612 0.4153 0.9999
3.750 0.8272 0.01317 0.00543 -0.0603 0.4033 1.0000
4.000 0.8497 0.01337 0.00557 -0.0593 0.3933 1.0000
4.250 0.8717 0.01359 0.00573 -0.0582 0.3849 1.0000
4.500 0.8940 0.01380 0.00591 -0.0572 0.3769 1.0000
4.750 0.9155 0.01406 0.00611 -0.0560 0.3688 1.0000
5.000 0.9371 0.01430 0.00632 -0.0549 0.3607 1.0000
5.250 0.9581 0.01457 0.00655 -0.0536 0.3536 1.0000
5.500 0.9790 0.01484 0.00680 -0.0524 0.3480 1.0000
5.750 0.9999 0.01510 0.00706 -0.0511 0.3411 1.0000
6.000 1.0194 0.01543 0.00733 -0.0497 0.3343 1.0000
6.250 1.0397 0.01570 0.00761 -0.0484 0.3277 1.0000
6.500 1.0590 0.01601 0.00791 -0.0469 0.3209 1.0000
6.750 1.0775 0.01635 0.00821 -0.0453 0.3153 1.0000
7.000 1.0971 0.01662 0.00854 -0.0439 0.3100 1.0000
7.250 1.1155 0.01694 0.00887 -0.0423 0.3049 1.0000
7.500 1.1327 0.01730 0.00921 -0.0405 0.3003 1.0000
7.750 1.1510 0.01760 0.00957 -0.0388 0.2956 1.0000
8.000 1.1682 0.01792 0.00993 -0.0371 0.2903 1.0000
8.250 1.1837 0.01829 0.01031 -0.0350 0.2853 1.0000
8.500 1.1992 0.01865 0.01070 -0.0330 0.2804 1.0000
8.750 1.2145 0.01899 0.01111 -0.0310 0.2748 1.0000
9.000 1.2273 0.01940 0.01154 -0.0285 0.2692 1.0000
9.250 1.2397 0.01981 0.01198 -0.0261 0.2638 1.0000
9.500 1.2515 0.02022 0.01245 -0.0236 0.2574 1.0000
9.750 1.2568 0.02070 0.01294 -0.0200 0.2515 1.0000
10.000 1.2638 0.02115 0.01345 -0.0168 0.2450 1.0000
10.250 1.2690 0.02172 0.01405 -0.0136 0.2379 1.0000
10.500 1.2749 0.02240 0.01475 -0.0108 0.2304 1.0000
10.750 1.2804 0.02321 0.01559 -0.0083 0.2222 1.0000
11.000 1.2861 0.02414 0.01656 -0.0061 0.2134 1.0000
11.250 1.2888 0.02534 0.01775 -0.0039 0.2044 1.0000
11.500 1.2937 0.02657 0.01900 -0.0022 0.1947 1.0000
11.750 1.2964 0.02803 0.02045 -0.0006 0.1863 1.0000
12.000 1.2992 0.02957 0.02200 0.0009 0.1790 1.0000
12.250 1.3023 0.03117 0.02361 0.0023 0.1732 1.0000
12.500 1.3059 0.03281 0.02528 0.0035 0.1678 1.0000
12.750 1.3070 0.03468 0.02715 0.0046 0.1633 1.0000
13.000 1.3112 0.03635 0.02888 0.0056 0.1591 1.0000
13.250 1.3146 0.03815 0.03072 0.0064 0.1551 1.0000
13.500 1.3161 0.04012 0.03271 0.0073 0.1517 1.0000
13.750 1.3167 0.04223 0.03484 0.0080 0.1480 1.0000
14.000 1.3205 0.04412 0.03681 0.0086 0.1439 1.0000
14.250 1.3207 0.04639 0.03910 0.0091 0.1397 1.0000
14.500 1.3209 0.04872 0.04145 0.0095 0.1368 1.0000
14.750 1.3230 0.05093 0.04371 0.0098 0.1338 1.0000
15.000 1.3269 0.05305 0.04594 0.0100 0.1308 1.0000
15.250 1.3289 0.05541 0.04838 0.0101 0.1279 1.0000
15.500 1.3293 0.05799 0.05100 0.0101 0.1252 1.0000
15.750 1.3292 0.06061 0.05363 0.0101 0.1226 1.0000
16.000 1.3319 0.06300 0.05611 0.0100 0.1205 1.0000
16.250 1.3348 0.06547 0.05871 0.0098 0.1183 1.0000
16.500 1.3353 0.06829 0.06164 0.0094 0.1155 1.0000
16.750 1.3348 0.07120 0.06462 0.0090 0.1130 1.0000
17.000 1.3326 0.07437 0.06783 0.0085 0.1103 1.0000
17.250 1.3315 0.07743 0.07094 0.0079 0.1079 1.0000
17.500 1.3304 0.08069 0.07436 0.0071 0.1053 1.0000
17.750 1.3276 0.08420 0.07800 0.0062 0.1023 1.0000
18.000 1.3228 0.08801 0.08189 0.0051 0.0992 1.0000
18.250 1.3178 0.09183 0.08573 0.0040 0.0966 1.0000
18.500 1.3143 0.09565 0.08972 0.0028 0.0935 1.0000
18.750 1.3088 0.09978 0.09400 0.0014 0.0900 1.0000
19.000 1.3015 0.10420 0.09851 -0.0002 0.0866 1.0000
19.250 1.2957 0.10845 0.10288 -0.0018 0.0832 1.0000
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Polar data table (+)
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