GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 A AIRFOIL (goe802a-il) Reynolds number: 500,000 Max Cl/Cd: 101.73 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802a-il-500000.txt Download as CSV file: xf-goe802a-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3150 0.09408 0.09188 -0.0245 1.0000 0.0225
-8.250 -0.3098 0.09100 0.08883 -0.0267 1.0000 0.0233
-8.000 -0.3166 0.08886 0.08676 -0.0280 1.0000 0.0237
-7.750 -0.2926 0.08325 0.08111 -0.0420 0.9913 0.0239
-7.500 -0.2644 0.07767 0.07546 -0.0528 0.9832 0.0239
-7.250 -0.2500 0.07332 0.07112 -0.0535 0.9773 0.0241
-7.000 -0.2327 0.07002 0.06782 -0.0552 0.9693 0.0243
-6.750 -0.2155 0.06694 0.06471 -0.0576 0.9589 0.0246
-6.500 -0.1983 0.06390 0.06162 -0.0602 0.9484 0.0250
-6.250 -0.1819 0.06087 0.05854 -0.0625 0.9364 0.0255
-6.000 -0.1636 0.05774 0.05532 -0.0649 0.9254 0.0261
-5.500 -0.1050 0.04990 0.04695 -0.0740 0.9038 0.0285
-5.250 -0.0890 0.04590 0.04287 -0.0746 0.8942 0.0288
-5.000 -0.0716 0.04342 0.04036 -0.0746 0.8839 0.0290
-4.750 -0.0517 0.04122 0.03808 -0.0750 0.8744 0.0294
-4.500 -0.0297 0.03907 0.03583 -0.0755 0.8646 0.0299
-4.250 -0.0058 0.03695 0.03358 -0.0761 0.8548 0.0307
-4.000 0.0278 0.03542 0.03157 -0.0765 0.8452 0.0336
-3.750 0.0514 0.03216 0.02811 -0.0770 0.8354 0.0340
-3.500 0.0736 0.02991 0.02581 -0.0772 0.8261 0.0345
-3.250 0.0980 0.02823 0.02407 -0.0775 0.8156 0.0351
-3.000 0.1234 0.02679 0.02247 -0.0775 0.8057 0.0363
-2.750 0.1556 0.02714 0.02234 -0.0767 0.7941 0.0394
-2.500 0.1791 0.02401 0.01915 -0.0772 0.7830 0.0401
-2.250 0.2044 0.02260 0.01766 -0.0772 0.7706 0.0410
-2.000 0.2310 0.02160 0.01653 -0.0772 0.7561 0.0428
-1.750 0.2600 0.02097 0.01556 -0.0767 0.7410 0.0462
-1.500 0.2860 0.01962 0.01414 -0.0769 0.7250 0.0471
-1.250 0.3153 0.02037 0.01458 -0.0762 0.7070 0.0516
-1.000 0.3415 0.01839 0.01247 -0.0763 0.6889 0.0526
-0.750 0.3681 0.01733 0.01130 -0.0764 0.6698 0.0540
-0.500 0.3979 0.01866 0.01226 -0.0756 0.6505 0.0581
-0.250 0.4238 0.01642 0.00997 -0.0759 0.6330 0.0590
0.000 0.4509 0.01564 0.00908 -0.0758 0.6154 0.0602
0.250 0.4787 0.01534 0.00863 -0.0756 0.5988 0.0631
0.500 0.5072 0.01561 0.00867 -0.0752 0.5831 0.0641
0.750 0.5333 0.01116 0.00385 -0.0744 0.5717 0.0394
1.000 0.5598 0.01073 0.00335 -0.0742 0.5574 0.0405
1.250 0.5873 0.01066 0.00326 -0.0741 0.5431 0.0419
1.500 0.6148 0.01061 0.00319 -0.0740 0.5294 0.0437
1.750 0.6421 0.01061 0.00315 -0.0739 0.5153 0.0459
2.000 0.6697 0.01085 0.00335 -0.0738 0.5001 0.0503
2.250 0.6974 0.01112 0.00355 -0.0736 0.4850 0.0550
2.500 0.7254 0.01143 0.00380 -0.0735 0.4705 0.0649
2.750 0.7535 0.01186 0.00412 -0.0735 0.4570 0.0771
3.000 0.7810 0.01224 0.00435 -0.0734 0.4438 0.0933
3.250 0.8073 0.01183 0.00396 -0.0733 0.4306 0.1025
3.500 0.8337 0.01140 0.00360 -0.0733 0.4191 0.1153
3.750 0.8604 0.01099 0.00330 -0.0734 0.4092 0.1275
4.000 0.8872 0.01103 0.00331 -0.0733 0.3991 0.1317
4.250 0.9143 0.01111 0.00339 -0.0733 0.3894 0.1342
4.500 0.9407 0.01127 0.00352 -0.0732 0.3782 0.1384
4.750 0.9674 0.01139 0.00368 -0.0731 0.3669 0.1882
5.000 0.9939 0.01155 0.00385 -0.0730 0.3573 0.1984
5.250 1.0204 0.01172 0.00403 -0.0729 0.3484 0.2095
5.500 1.0468 0.01187 0.00422 -0.0728 0.3399 0.2242
5.750 1.0729 0.01205 0.00442 -0.0726 0.3304 0.2430
6.000 1.0904 0.01092 0.00474 -0.0708 0.3229 0.8947
6.250 1.1214 0.01108 0.00493 -0.0717 0.3117 1.0000
6.500 1.1475 0.01128 0.00514 -0.0716 0.3019 1.0000
6.750 1.1727 0.01156 0.00538 -0.0713 0.2913 1.0000
7.000 1.1980 0.01183 0.00561 -0.0710 0.2781 1.0000
7.250 1.2224 0.01217 0.00587 -0.0707 0.2589 1.0000
7.500 1.2463 0.01256 0.00616 -0.0702 0.2353 1.0000
8.000 1.2911 0.01361 0.00696 -0.0690 0.1906 1.0000
8.250 1.3131 0.01415 0.00743 -0.0683 0.1754 1.0000
8.750 1.3574 0.01513 0.00833 -0.0670 0.1533 1.0000
9.000 1.3789 0.01565 0.00882 -0.0663 0.1435 1.0000
9.250 1.4003 0.01614 0.00928 -0.0656 0.1343 1.0000
9.500 1.4219 0.01660 0.00976 -0.0649 0.1261 1.0000
9.750 1.4417 0.01719 0.01030 -0.0639 0.1163 1.0000
10.000 1.4621 0.01769 0.01079 -0.0630 0.1064 1.0000
10.250 1.4807 0.01830 0.01137 -0.0620 0.0950 1.0000
10.500 1.4973 0.01903 0.01203 -0.0606 0.0823 1.0000
10.750 1.5122 0.01981 0.01275 -0.0590 0.0721 1.0000
11.000 1.5242 0.02065 0.01354 -0.0570 0.0634 1.0000
11.250 1.5347 0.02151 0.01439 -0.0547 0.0564 1.0000
11.500 1.5455 0.02239 0.01528 -0.0526 0.0486 1.0000
11.750 1.5503 0.02373 0.01653 -0.0500 0.0318 1.0000
12.000 1.5479 0.02567 0.01838 -0.0470 0.0222 1.0000
12.250 1.5538 0.02712 0.01990 -0.0451 0.0201 1.0000
12.500 1.5601 0.02861 0.02149 -0.0434 0.0191 1.0000
12.750 1.5648 0.03030 0.02330 -0.0418 0.0184 1.0000
13.000 1.5675 0.03227 0.02539 -0.0403 0.0178 1.0000
13.250 1.5683 0.03451 0.02774 -0.0390 0.0172 1.0000
13.500 1.5668 0.03711 0.03047 -0.0379 0.0167 1.0000
13.750 1.5626 0.04013 0.03362 -0.0371 0.0164 1.0000
14.000 1.5620 0.04292 0.03653 -0.0367 0.0162 1.0000
14.250 1.5597 0.04602 0.03976 -0.0365 0.0159 1.0000
14.500 1.5553 0.04950 0.04337 -0.0365 0.0157 1.0000
14.750 1.5493 0.05335 0.04735 -0.0369 0.0155 1.0000
15.000 1.5412 0.05756 0.05170 -0.0375 0.0152 1.0000
15.250 1.5321 0.06210 0.05637 -0.0384 0.0150 1.0000
15.500 1.5214 0.06700 0.06139 -0.0395 0.0148 1.0000
15.750 1.5099 0.07208 0.06661 -0.0407 0.0147 1.0000
16.000 1.4973 0.07745 0.07210 -0.0422 0.0145 1.0000
16.250 1.4841 0.08300 0.07777 -0.0438 0.0144 1.0000
16.500 1.4704 0.08870 0.08359 -0.0455 0.0143 1.0000
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