GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 200,000 Max Cl/Cd: 99.07 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe499-il-200000-n5.txt Download as CSV file: xf-goe499-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 499 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2095 0.09106 0.08749 -0.0669 0.9700 0.0187
-8.000 -0.1948 0.08714 0.08357 -0.0714 0.9667 0.0198
-7.750 -0.1859 0.08321 0.07966 -0.0754 0.9604 0.0209
-7.500 -0.1740 0.07893 0.07537 -0.0802 0.9551 0.0213
-7.250 -0.1587 0.07404 0.07048 -0.0864 0.9495 0.0219
-7.000 -0.1434 0.06882 0.06527 -0.0931 0.9432 0.0228
-6.750 -0.1226 0.06714 0.06355 -0.0952 0.9408 0.0243
-6.500 -0.0975 0.06498 0.06133 -0.0992 0.9388 0.0272
-6.250 -0.0828 0.06117 0.05750 -0.1038 0.9310 0.0282
-6.000 -0.0533 0.05577 0.05203 -0.1134 0.9269 0.0297
-5.750 -0.0183 0.04884 0.04500 -0.1260 0.9215 0.0323
-5.500 0.0336 0.03665 0.03246 -0.1463 0.9160 0.0332
-5.250 0.0828 0.02770 0.02285 -0.1611 0.9135 0.0362
-5.000 0.1224 0.02381 0.01838 -0.1670 0.9118 0.0371
-4.750 0.1539 0.02159 0.01573 -0.1694 0.9085 0.0379
-4.500 0.1831 0.02000 0.01376 -0.1707 0.9049 0.0383
-4.250 0.2137 0.01892 0.01240 -0.1719 0.9020 0.0397
-4.000 0.2460 0.01785 0.01105 -0.1732 0.8994 0.0407
-3.750 0.2798 0.01669 0.00959 -0.1746 0.8970 0.0403
-3.500 0.3055 0.01595 0.00865 -0.1744 0.8912 0.0400
-3.250 0.3356 0.01520 0.00773 -0.1748 0.8869 0.0398
-3.000 0.3674 0.01451 0.00691 -0.1756 0.8838 0.0397
-2.750 0.3942 0.01405 0.00635 -0.1754 0.8786 0.0397
-2.500 0.4228 0.01362 0.00584 -0.1756 0.8740 0.0399
-2.250 0.4535 0.01319 0.00533 -0.1761 0.8705 0.0402
-2.000 0.4809 0.01291 0.00499 -0.1760 0.8653 0.0408
-1.750 0.5092 0.01265 0.00465 -0.1760 0.8602 0.0418
-1.500 0.5397 0.01236 0.00427 -0.1764 0.8561 0.0432
-1.250 0.5659 0.01221 0.00407 -0.1760 0.8496 0.0453
-1.000 0.5948 0.01200 0.00382 -0.1761 0.8448 0.0501
-0.750 0.6244 0.01168 0.00366 -0.1764 0.8411 0.0832
-0.500 0.6505 0.01153 0.00369 -0.1762 0.8353 0.1393
-0.250 0.6788 0.01137 0.00373 -0.1763 0.8308 0.2022
0.000 0.7071 0.01126 0.00374 -0.1764 0.8264 0.2466
0.250 0.7332 0.01123 0.00380 -0.1761 0.8202 0.2760
0.500 0.7617 0.01110 0.00379 -0.1761 0.8152 0.3132
0.750 0.7878 0.01090 0.00395 -0.1759 0.8085 0.4129
1.000 0.8148 0.01073 0.00404 -0.1756 0.8022 0.5211
1.250 0.8410 0.01060 0.00413 -0.1752 0.7956 0.6014
1.500 0.8646 0.00995 0.00406 -0.1739 0.7877 1.0000
1.750 0.8910 0.01001 0.00410 -0.1734 0.7777 1.0000
2.000 0.9179 0.01005 0.00414 -0.1730 0.7672 1.0000
2.250 0.9448 0.01010 0.00416 -0.1726 0.7558 1.0000
2.500 0.9710 0.01017 0.00424 -0.1721 0.7433 1.0000
2.750 0.9968 0.01024 0.00432 -0.1715 0.7272 1.0000
3.000 1.0204 0.01030 0.00423 -0.1701 0.6797 1.0000
3.250 1.0400 0.01073 0.00416 -0.1679 0.5958 1.0000
3.500 1.0587 0.01134 0.00443 -0.1659 0.5417 1.0000
3.750 1.0724 0.01231 0.00492 -0.1632 0.4687 1.0000
4.000 1.0884 0.01316 0.00544 -0.1610 0.4054 1.0000
4.250 1.0929 0.01503 0.00630 -0.1573 0.2298 1.0000
4.500 1.0947 0.01763 0.00779 -0.1534 0.0325 1.0000
4.750 1.1145 0.01837 0.00854 -0.1519 0.0231 1.0000
5.000 1.1342 0.01912 0.00942 -0.1504 0.0201 1.0000
5.250 1.1542 0.01979 0.01022 -0.1489 0.0186 1.0000
5.500 1.1731 0.02053 0.01111 -0.1473 0.0165 1.0000
5.750 1.1899 0.02144 0.01214 -0.1454 0.0155 1.0000
6.000 1.2045 0.02250 0.01330 -0.1431 0.0146 1.0000
6.250 1.2167 0.02365 0.01455 -0.1404 0.0140 1.0000
6.500 1.2274 0.02492 0.01588 -0.1376 0.0133 1.0000
6.750 1.2367 0.02650 0.01751 -0.1347 0.0122 1.0000
7.000 1.2485 0.02915 0.02024 -0.1323 0.0111 1.0000
7.250 1.2689 0.03053 0.02172 -0.1310 0.0108 1.0000
7.500 1.2926 0.03219 0.02349 -0.1303 0.0105 1.0000
7.750 1.3199 0.03418 0.02562 -0.1301 0.0102 1.0000
8.000 1.3480 0.03647 0.02812 -0.1301 0.0100 1.0000
8.250 1.3730 0.03896 0.03085 -0.1295 0.0098 1.0000
8.500 1.3926 0.04105 0.03320 -0.1281 0.0093 1.0000
8.750 1.4086 0.04292 0.03529 -0.1264 0.0087 1.0000
9.000 1.4223 0.04492 0.03755 -0.1245 0.0082 1.0000
9.250 1.4343 0.04751 0.04041 -0.1224 0.0079 1.0000
9.500 1.4424 0.05041 0.04361 -0.1198 0.0078 1.0000
9.750 1.4452 0.05343 0.04695 -0.1165 0.0078 1.0000
10.000 1.4433 0.05654 0.05037 -0.1128 0.0078 1.0000
10.250 1.4372 0.05980 0.05393 -0.1089 0.0078 1.0000
10.500 1.4273 0.06341 0.05787 -0.1050 0.0079 1.0000
10.750 1.4145 0.06731 0.06208 -0.1014 0.0080 1.0000
11.000 1.3995 0.07153 0.06659 -0.0984 0.0081 1.0000
11.250 1.3826 0.07605 0.07138 -0.0959 0.0082 1.0000
11.500 1.3640 0.08095 0.07655 -0.0943 0.0083 1.0000
11.750 1.3449 0.08616 0.08200 -0.0935 0.0084 1.0000
12.000 1.3249 0.09184 0.08791 -0.0936 0.0085 1.0000
12.250 1.3040 0.09805 0.09432 -0.0947 0.0086 1.0000
12.500 1.2836 0.10470 0.10117 -0.0970 0.0087 1.0000
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Polar data table (+)
Polar graphs
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