GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 500,000 Max Cl/Cd: 121.96 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe446-il-500000.txt Download as CSV file: xf-goe446-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 446 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0327 0.08631 0.08371 -0.1028 0.9234 0.0369
-8.750 -0.0472 0.08069 0.07806 -0.1100 0.9041 0.0390
-8.500 -0.0430 0.07722 0.07455 -0.1100 0.8927 0.0393
-8.250 -0.0324 0.07521 0.07250 -0.1096 0.8808 0.0396
-8.000 -0.0209 0.07330 0.07054 -0.1096 0.8693 0.0400
-7.750 -0.0103 0.07124 0.06843 -0.1101 0.8582 0.0404
-7.250 0.0089 0.06640 0.06348 -0.1139 0.8370 0.0420
-7.000 0.0189 0.05706 0.05400 -0.1308 0.8263 0.0456
-6.750 0.0350 0.05540 0.05230 -0.1311 0.8189 0.0460
-6.500 0.0281 0.02586 0.02142 -0.1560 0.8109 0.0393
-6.250 0.0487 0.02288 0.01818 -0.1566 0.8044 0.0384
-5.750 0.0946 0.01796 0.01238 -0.1573 0.7922 0.0382
-5.500 0.1204 0.01665 0.01076 -0.1574 0.7863 0.0382
-5.250 0.1472 0.01570 0.00955 -0.1574 0.7811 0.0384
-5.000 0.1741 0.01492 0.00860 -0.1574 0.7754 0.0386
-4.750 0.2014 0.01431 0.00783 -0.1574 0.7699 0.0388
-4.500 0.2293 0.01383 0.00718 -0.1574 0.7646 0.0390
-4.250 0.2561 0.01302 0.00628 -0.1573 0.7591 0.0395
-4.000 0.2835 0.01243 0.00562 -0.1574 0.7544 0.0401
-3.750 0.3115 0.01207 0.00521 -0.1575 0.7504 0.0410
-3.500 0.3396 0.01179 0.00491 -0.1576 0.7463 0.0421
-3.250 0.3674 0.01150 0.00459 -0.1576 0.7417 0.0430
-3.000 0.3955 0.01125 0.00429 -0.1576 0.7373 0.0439
-2.750 0.4240 0.01107 0.00403 -0.1577 0.7331 0.0449
-2.500 0.4520 0.01078 0.00375 -0.1578 0.7290 0.0466
-2.250 0.4800 0.01060 0.00358 -0.1578 0.7247 0.0488
-2.000 0.5083 0.01046 0.00342 -0.1579 0.7205 0.0517
-1.750 0.5370 0.01034 0.00329 -0.1580 0.7165 0.0591
-1.500 0.5651 0.01024 0.00331 -0.1581 0.7121 0.0811
-1.250 0.5931 0.01025 0.00337 -0.1581 0.7073 0.0962
-1.000 0.6214 0.01032 0.00339 -0.1582 0.7027 0.1037
-0.750 0.6499 0.01029 0.00335 -0.1584 0.6983 0.1107
-0.500 0.6775 0.01028 0.00336 -0.1583 0.6936 0.1166
-0.250 0.7053 0.01023 0.00332 -0.1583 0.6887 0.1225
0.000 0.7335 0.01021 0.00328 -0.1584 0.6841 0.1291
0.250 0.7613 0.01021 0.00328 -0.1585 0.6793 0.1346
0.500 0.7887 0.01012 0.00324 -0.1584 0.6737 0.1424
0.750 0.8164 0.01011 0.00321 -0.1584 0.6684 0.1515
1.000 0.8439 0.01005 0.00321 -0.1584 0.6628 0.1660
1.250 0.8710 0.00995 0.00321 -0.1583 0.6564 0.1909
1.500 0.8981 0.00957 0.00327 -0.1585 0.6506 0.3724
1.750 0.9195 0.00834 0.00346 -0.1571 0.6445 1.0000
2.000 0.9462 0.00842 0.00347 -0.1569 0.6375 1.0000
2.250 0.9729 0.00852 0.00350 -0.1566 0.6308 1.0000
2.500 0.9991 0.00860 0.00355 -0.1563 0.6226 1.0000
2.750 1.0252 0.00872 0.00360 -0.1560 0.6147 1.0000
3.000 1.0508 0.00882 0.00367 -0.1556 0.6050 1.0000
3.250 1.0763 0.00895 0.00375 -0.1552 0.5956 1.0000
3.500 1.1012 0.00910 0.00383 -0.1546 0.5855 1.0000
3.750 1.1260 0.00924 0.00395 -0.1541 0.5743 1.0000
4.000 1.1501 0.00943 0.00408 -0.1534 0.5623 1.0000
4.250 1.1733 0.00964 0.00422 -0.1526 0.5494 1.0000
4.500 1.1957 0.00989 0.00438 -0.1516 0.5359 1.0000
4.750 1.2186 0.01013 0.00457 -0.1508 0.5231 1.0000
5.000 1.2414 0.01037 0.00477 -0.1499 0.5117 1.0000
5.250 1.2636 0.01065 0.00499 -0.1490 0.5013 1.0000
5.500 1.2851 0.01094 0.00523 -0.1479 0.4903 1.0000
5.750 1.3064 0.01122 0.00547 -0.1468 0.4786 1.0000
6.000 1.3267 0.01153 0.00573 -0.1455 0.4678 1.0000
6.250 1.3470 0.01183 0.00599 -0.1442 0.4594 1.0000
6.500 1.3674 0.01211 0.00627 -0.1429 0.4528 1.0000
6.750 1.3878 0.01239 0.00655 -0.1417 0.4455 1.0000
7.000 1.4066 0.01274 0.00687 -0.1402 0.4375 1.0000
7.250 1.4255 0.01307 0.00720 -0.1387 0.4281 1.0000
7.500 1.4442 0.01343 0.00756 -0.1373 0.4202 1.0000
7.750 1.4634 0.01377 0.00791 -0.1359 0.4121 1.0000
8.000 1.4814 0.01417 0.00831 -0.1344 0.4038 1.0000
8.250 1.4991 0.01457 0.00872 -0.1329 0.3945 1.0000
8.500 1.5172 0.01498 0.00915 -0.1314 0.3859 1.0000
8.750 1.5326 0.01551 0.00965 -0.1296 0.3753 1.0000
9.000 1.5499 0.01596 0.01014 -0.1281 0.3634 1.0000
9.250 1.5649 0.01654 0.01071 -0.1263 0.3498 1.0000
9.500 1.5767 0.01729 0.01141 -0.1241 0.3309 1.0000
9.750 1.5827 0.01838 0.01237 -0.1211 0.3012 1.0000
10.000 1.5806 0.02002 0.01379 -0.1173 0.2627 1.0000
10.250 1.5753 0.02199 0.01553 -0.1132 0.2255 1.0000
10.500 1.5723 0.02394 0.01732 -0.1097 0.1961 1.0000
10.750 1.5719 0.02581 0.01907 -0.1068 0.1728 1.0000
11.000 1.5734 0.02764 0.02081 -0.1043 0.1538 1.0000
11.250 1.5756 0.02947 0.02258 -0.1019 0.1385 1.0000
11.500 1.5780 0.03134 0.02441 -0.0998 0.1250 1.0000
11.750 1.5785 0.03346 0.02645 -0.0976 0.1106 1.0000
12.000 1.5783 0.03570 0.02863 -0.0955 0.0952 1.0000
12.250 1.5721 0.03855 0.03133 -0.0932 0.0696 1.0000
12.500 1.5519 0.04282 0.03538 -0.0901 0.0384 1.0000
12.750 1.5480 0.04568 0.03827 -0.0883 0.0330 1.0000
13.000 1.5465 0.04842 0.04106 -0.0868 0.0303 1.0000
13.250 1.5495 0.05075 0.04349 -0.0856 0.0289 1.0000
13.500 1.5500 0.05339 0.04621 -0.0845 0.0277 1.0000
13.750 1.5478 0.05637 0.04927 -0.0833 0.0266 1.0000
14.000 1.5421 0.05982 0.05280 -0.0821 0.0256 1.0000
14.250 1.5443 0.06246 0.05554 -0.0814 0.0250 1.0000
14.500 1.5447 0.06534 0.05851 -0.0807 0.0243 1.0000
14.750 1.5433 0.06847 0.06173 -0.0800 0.0236 1.0000
15.000 1.5407 0.07180 0.06514 -0.0794 0.0230 1.0000
15.250 1.5361 0.07546 0.06888 -0.0790 0.0224 1.0000
15.500 1.5279 0.07964 0.07316 -0.0786 0.0219 1.0000
15.750 1.5167 0.08427 0.07788 -0.0784 0.0215 1.0000
16.000 1.5163 0.08754 0.08124 -0.0783 0.0212 1.0000
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