GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 481A AIRFOIL (goe481a-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.75 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe481a-il-1000000.txt Download as CSV file: xf-goe481a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 481A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7486 0.03644 0.03330 -0.1468 0.9627 0.0429
-13.250 -0.7508 0.03430 0.03104 -0.1463 0.9602 0.0431
-13.000 -0.7433 0.03245 0.02906 -0.1461 0.9588 0.0432
-12.750 -0.7528 0.03143 0.02798 -0.1408 0.9521 0.0433
-12.500 -0.7398 0.03025 0.02672 -0.1397 0.9496 0.0435
-12.250 -0.7217 0.02903 0.02541 -0.1395 0.9482 0.0437
-12.000 -0.7000 0.02785 0.02414 -0.1397 0.9470 0.0440
-11.750 -0.6749 0.02659 0.02278 -0.1404 0.9461 0.0442
-11.500 -0.6462 0.02543 0.02151 -0.1417 0.9454 0.0446
-11.250 -0.6502 0.02467 0.02067 -0.1360 0.9376 0.0447
-11.000 -0.6254 0.02364 0.01955 -0.1362 0.9358 0.0450
-10.750 -0.5987 0.02266 0.01847 -0.1366 0.9346 0.0453
-10.500 -0.5707 0.02173 0.01745 -0.1371 0.9337 0.0456
-10.250 -0.5417 0.02081 0.01643 -0.1378 0.9329 0.0459
-10.000 -0.5112 0.01999 0.01551 -0.1387 0.9323 0.0462
-9.750 -0.5041 0.01953 0.01498 -0.1346 0.9261 0.0464
-9.500 -0.4808 0.01904 0.01441 -0.1338 0.9236 0.0467
-9.250 -0.4547 0.01842 0.01371 -0.1335 0.9222 0.0468
-9.000 -0.4318 0.01719 0.01237 -0.1331 0.9210 0.0473
-8.750 -0.4043 0.01636 0.01151 -0.1332 0.9201 0.0478
-8.500 -0.3744 0.01577 0.01089 -0.1336 0.9193 0.0481
-8.250 -0.3426 0.01523 0.01033 -0.1344 0.9186 0.0485
-8.000 -0.3104 0.01470 0.00978 -0.1353 0.9179 0.0489
-7.750 -0.2974 0.01443 0.00946 -0.1321 0.9130 0.0492
-7.500 -0.2755 0.01405 0.00905 -0.1307 0.9093 0.0496
-7.250 -0.2450 0.01359 0.00855 -0.1311 0.9074 0.0500
-7.000 -0.2128 0.01311 0.00803 -0.1319 0.9056 0.0504
-6.750 -0.1798 0.01265 0.00752 -0.1328 0.9040 0.0509
-6.500 -0.1415 0.01224 0.00706 -0.1348 0.9026 0.0514
-6.250 -0.1264 0.01204 0.00683 -0.1319 0.8964 0.0516
-6.000 -0.1008 0.01180 0.00655 -0.1311 0.8916 0.0519
-5.750 -0.0681 0.01109 0.00580 -0.1321 0.8884 0.0528
-5.500 -0.0243 0.01061 0.00531 -0.1354 0.8857 0.0536
-5.250 -0.0209 0.01052 0.00521 -0.1299 0.8756 0.0538
-5.000 0.0198 0.01016 0.00481 -0.1324 0.8701 0.0544
-4.750 0.0349 0.01004 0.00466 -0.1294 0.8591 0.0551
-4.500 0.0671 0.00979 0.00435 -0.1300 0.8489 0.0557
-4.250 0.0916 0.00962 0.00413 -0.1290 0.8355 0.0563
-4.000 0.1137 0.00950 0.00394 -0.1275 0.8190 0.0568
-3.750 0.1361 0.00944 0.00376 -0.1260 0.7973 0.0573
-3.500 0.1508 0.00936 0.00355 -0.1229 0.7675 0.0578
-3.250 0.1606 0.00939 0.00342 -0.1188 0.7333 0.0586
-2.750 0.1835 0.00954 0.00331 -0.1113 0.6775 0.0601
-2.500 0.1985 0.00962 0.00330 -0.1083 0.6557 0.0609
-2.250 0.2138 0.00969 0.00327 -0.1054 0.6363 0.0618
-2.000 0.2302 0.00975 0.00325 -0.1028 0.6201 0.0627
-1.750 0.2487 0.00980 0.00322 -0.1006 0.6057 0.0633
-1.500 0.2678 0.00973 0.00312 -0.0985 0.5939 0.0649
-1.000 0.3085 0.00973 0.00305 -0.0949 0.5728 0.0678
-0.750 0.3283 0.00978 0.00303 -0.0930 0.5628 0.0693
-0.500 0.3502 0.00974 0.00299 -0.0915 0.5545 0.0720
-0.250 0.3703 0.00976 0.00298 -0.0897 0.5446 0.0751
0.000 0.3913 0.00975 0.00297 -0.0881 0.5350 0.0799
0.250 0.4118 0.00974 0.00299 -0.0864 0.5271 0.0898
0.500 0.4320 0.00978 0.00307 -0.0846 0.5197 0.1066
0.750 0.4549 0.00983 0.00315 -0.0834 0.5123 0.1176
1.000 0.4760 0.00994 0.00323 -0.0818 0.5043 0.1235
1.250 0.4987 0.01002 0.00331 -0.0805 0.4976 0.1283
1.500 0.5217 0.01012 0.00339 -0.0794 0.4896 0.1316
1.750 0.5420 0.01022 0.00345 -0.0777 0.4817 0.1351
2.000 0.5657 0.01027 0.00352 -0.0766 0.4759 0.1386
2.250 0.5879 0.01036 0.00359 -0.0753 0.4680 0.1413
2.500 0.6090 0.01050 0.00368 -0.0738 0.4606 0.1437
2.750 0.6322 0.01055 0.00374 -0.0727 0.4546 0.1455
3.000 0.6528 0.01061 0.00379 -0.0711 0.4474 0.1489
3.250 0.6731 0.01072 0.00388 -0.0695 0.4399 0.1514
3.500 0.6954 0.01080 0.00396 -0.0682 0.4322 0.1544
3.750 0.7155 0.01096 0.00407 -0.0666 0.4237 0.1571
4.000 0.7380 0.01106 0.00417 -0.0654 0.4164 0.1589
4.250 0.7584 0.01116 0.00424 -0.0639 0.4074 0.1633
4.500 0.7796 0.01127 0.00436 -0.0625 0.4000 0.1668
4.750 0.8010 0.01140 0.00447 -0.0612 0.3920 0.1705
5.000 0.8203 0.01159 0.00461 -0.0595 0.3833 0.1723
5.250 0.8421 0.01171 0.00473 -0.0582 0.3763 0.1743
5.500 0.8622 0.01187 0.00488 -0.0567 0.3689 0.1798
5.750 0.8835 0.01202 0.00504 -0.0555 0.3623 0.1846
6.000 1.1021 0.01151 0.00630 -0.0984 0.3417 1.0000
6.250 1.1213 0.01178 0.00650 -0.0967 0.3330 1.0000
6.500 1.1414 0.01201 0.00670 -0.0952 0.3267 1.0000
6.750 1.1625 0.01222 0.00688 -0.0939 0.3209 1.0000
7.000 1.1824 0.01247 0.00710 -0.0924 0.3149 1.0000
7.250 1.2025 0.01273 0.00733 -0.0910 0.3092 1.0000
7.500 1.2232 0.01295 0.00754 -0.0897 0.3036 1.0000
7.750 1.2420 0.01326 0.00781 -0.0881 0.2969 1.0000
8.000 1.2614 0.01355 0.00807 -0.0866 0.2902 1.0000
8.250 1.2809 0.01385 0.00834 -0.0852 0.2823 1.0000
8.500 1.2992 0.01420 0.00865 -0.0836 0.2743 1.0000
8.750 1.3181 0.01452 0.00895 -0.0821 0.2657 1.0000
9.000 1.3348 0.01494 0.00932 -0.0803 0.2562 1.0000
9.250 1.3511 0.01539 0.00971 -0.0784 0.2443 1.0000
9.500 1.3673 0.01586 0.01012 -0.0766 0.2318 1.0000
9.750 1.3812 0.01643 0.01062 -0.0745 0.2183 1.0000
10.000 1.3935 0.01710 0.01120 -0.0722 0.2038 1.0000
10.250 1.4060 0.01776 0.01180 -0.0699 0.1923 1.0000
10.500 1.4193 0.01839 0.01239 -0.0678 0.1848 1.0000
10.750 1.4331 0.01900 0.01298 -0.0659 0.1793 1.0000
11.000 1.4475 0.01961 0.01358 -0.0641 0.1739 1.0000
11.250 1.4605 0.02028 0.01424 -0.0621 0.1700 1.0000
11.500 1.4734 0.02098 0.01494 -0.0602 0.1658 1.0000
11.750 1.4894 0.02152 0.01550 -0.0587 0.1639 1.0000
12.000 1.5036 0.02217 0.01618 -0.0570 0.1616 1.0000
12.250 1.5170 0.02288 0.01690 -0.0553 0.1591 1.0000
12.500 1.5289 0.02369 0.01772 -0.0535 0.1564 1.0000
12.750 1.5379 0.02469 0.01872 -0.0514 0.1525 1.0000
13.000 1.5541 0.02529 0.01937 -0.0502 0.1509 1.0000
13.250 1.5674 0.02606 0.02017 -0.0487 0.1483 1.0000
13.500 1.5787 0.02698 0.02110 -0.0470 0.1452 1.0000
13.750 1.5883 0.02804 0.02218 -0.0453 0.1425 1.0000
14.000 1.5965 0.02923 0.02338 -0.0435 0.1395 1.0000
14.250 1.6110 0.03001 0.02422 -0.0424 0.1371 1.0000
14.500 1.6225 0.03102 0.02526 -0.0410 0.1342 1.0000
14.750 1.6301 0.03233 0.02658 -0.0395 0.1304 1.0000
15.000 1.6374 0.03370 0.02797 -0.0380 0.1266 1.0000
15.250 1.6467 0.03497 0.02926 -0.0367 0.1221 1.0000
15.500 1.6497 0.03677 0.03104 -0.0351 0.1155 1.0000
15.750 1.6523 0.03866 0.03292 -0.0336 0.1073 1.0000
16.000 1.6516 0.04090 0.03515 -0.0322 0.0996 1.0000
16.250 1.6482 0.04346 0.03770 -0.0307 0.0933 1.0000
16.500 1.6432 0.04627 0.04051 -0.0294 0.0883 1.0000
16.750 1.6419 0.04881 0.04311 -0.0285 0.0854 1.0000
17.000 1.6400 0.05148 0.04582 -0.0276 0.0833 1.0000
17.250 1.6354 0.05447 0.04885 -0.0269 0.0811 1.0000
17.500 1.6302 0.05760 0.05204 -0.0263 0.0792 1.0000
17.750 1.6290 0.06037 0.05488 -0.0259 0.0777 1.0000
18.000 1.6272 0.06322 0.05780 -0.0255 0.0768 1.0000
18.250 1.6239 0.06628 0.06092 -0.0253 0.0758 1.0000
18.500 1.6173 0.06974 0.06444 -0.0251 0.0744 1.0000
18.750 1.6088 0.07350 0.06826 -0.0251 0.0729 1.0000
19.000 1.5997 0.07739 0.07222 -0.0252 0.0719 1.0000
19.250 1.5966 0.08059 0.07550 -0.0253 0.0711 1.0000
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