GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.92 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe495-il-1000000-n5.txt Download as CSV file: xf-goe495-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 495 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3602 0.11055 0.10889 -0.0315 1.0000 0.0036
-9.250 -0.4156 0.02064 0.01795 -0.1352 0.9671 0.0043
-9.000 -0.3876 0.01804 0.01502 -0.1380 0.9620 0.0044
-8.750 -0.3583 0.01632 0.01304 -0.1399 0.9570 0.0046
-8.500 -0.3277 0.01512 0.01163 -0.1415 0.9527 0.0049
-8.250 -0.3001 0.01419 0.01053 -0.1421 0.9457 0.0051
-8.000 -0.2705 0.01307 0.00918 -0.1432 0.9395 0.0053
-7.750 -0.2430 0.01209 0.00800 -0.1437 0.9310 0.0057
-7.500 -0.2147 0.01145 0.00721 -0.1442 0.9229 0.0060
-7.250 -0.1870 0.01092 0.00656 -0.1443 0.9132 0.0064
-7.000 -0.1595 0.01044 0.00594 -0.1444 0.9034 0.0068
-6.750 -0.1321 0.01002 0.00538 -0.1444 0.8932 0.0072
-6.500 -0.1050 0.00968 0.00489 -0.1443 0.8815 0.0076
-6.250 -0.0781 0.00924 0.00431 -0.1442 0.8694 0.0085
-6.000 -0.0510 0.00895 0.00392 -0.1441 0.8589 0.0095
-5.750 -0.0237 0.00871 0.00359 -0.1439 0.8507 0.0106
-5.500 0.0037 0.00844 0.00323 -0.1438 0.8434 0.0119
-5.250 0.0312 0.00824 0.00302 -0.1438 0.8370 0.0142
-5.000 0.0588 0.00810 0.00283 -0.1437 0.8303 0.0161
-4.750 0.0864 0.00797 0.00268 -0.1436 0.8247 0.0187
-4.500 0.1141 0.00790 0.00260 -0.1435 0.8189 0.0213
-4.250 0.1417 0.00783 0.00248 -0.1434 0.8133 0.0233
-4.000 0.1695 0.00780 0.00241 -0.1433 0.8081 0.0245
-3.750 0.1973 0.00778 0.00236 -0.1432 0.8026 0.0251
-3.250 0.2528 0.00736 0.00181 -0.1431 0.7922 0.0278
-3.000 0.2806 0.00722 0.00161 -0.1430 0.7866 0.0292
-2.750 0.3083 0.00711 0.00145 -0.1429 0.7816 0.0298
-2.500 0.3363 0.00700 0.00130 -0.1428 0.7759 0.0303
-2.250 0.3640 0.00692 0.00117 -0.1427 0.7699 0.0311
-2.000 0.3918 0.00684 0.00107 -0.1426 0.7644 0.0321
-1.750 0.4196 0.00677 0.00097 -0.1425 0.7580 0.0330
-1.500 0.4472 0.00673 0.00089 -0.1424 0.7517 0.0346
-1.250 0.4750 0.00667 0.00082 -0.1423 0.7444 0.0390
-1.000 0.5024 0.00655 0.00077 -0.1422 0.7369 0.0665
-0.750 0.5296 0.00647 0.00074 -0.1420 0.7253 0.1009
-0.500 0.5563 0.00644 0.00072 -0.1417 0.7072 0.1258
-0.250 0.5825 0.00648 0.00072 -0.1413 0.6845 0.1446
0.000 0.6089 0.00651 0.00074 -0.1410 0.6660 0.1681
0.250 0.6357 0.00654 0.00076 -0.1407 0.6502 0.1888
0.500 0.6624 0.00656 0.00080 -0.1404 0.6352 0.2156
0.750 0.6889 0.00658 0.00086 -0.1402 0.6177 0.2542
1.250 0.7416 0.00663 0.00103 -0.1396 0.5826 0.3608
1.500 0.7679 0.00665 0.00113 -0.1393 0.5668 0.4166
1.750 0.7945 0.00669 0.00123 -0.1391 0.5535 0.4613
2.250 0.8456 0.00689 0.00150 -0.1383 0.5069 0.5697
2.500 0.8708 0.00693 0.00166 -0.1378 0.4821 0.6600
3.000 0.9151 0.00721 0.00208 -0.1356 0.3727 1.0000
3.250 0.9377 0.00774 0.00234 -0.1347 0.3169 1.0000
3.500 0.9614 0.00817 0.00258 -0.1340 0.2762 1.0000
3.750 0.9845 0.00867 0.00286 -0.1332 0.2272 1.0000
4.000 1.0065 0.00928 0.00321 -0.1323 0.1734 1.0000
4.250 1.0311 0.00961 0.00345 -0.1317 0.1538 1.0000
4.500 1.0559 0.00990 0.00368 -0.1312 0.1383 1.0000
4.750 1.0803 0.01024 0.00395 -0.1306 0.1188 1.0000
5.000 1.1021 0.01085 0.00432 -0.1296 0.0768 1.0000
5.250 1.1240 0.01143 0.00474 -0.1287 0.0459 1.0000
5.500 1.1480 0.01178 0.00505 -0.1280 0.0377 1.0000
5.750 1.1721 0.01211 0.00537 -0.1274 0.0323 1.0000
6.000 1.1967 0.01238 0.00566 -0.1268 0.0301 1.0000
6.250 1.2205 0.01271 0.00599 -0.1261 0.0262 1.0000
6.500 1.2441 0.01306 0.00633 -0.1254 0.0223 1.0000
6.750 1.2672 0.01345 0.00670 -0.1246 0.0168 1.0000
7.000 1.2896 0.01388 0.00712 -0.1238 0.0123 1.0000
7.250 1.3118 0.01435 0.00757 -0.1228 0.0095 1.0000
7.500 1.3342 0.01475 0.00801 -0.1219 0.0084 1.0000
7.750 1.3556 0.01525 0.00852 -0.1209 0.0071 1.0000
8.000 1.3769 0.01574 0.00905 -0.1198 0.0063 1.0000
8.250 1.3982 0.01620 0.00956 -0.1188 0.0058 1.0000
8.500 1.4189 0.01670 0.01010 -0.1177 0.0053 1.0000
8.750 1.4386 0.01726 0.01071 -0.1164 0.0049 1.0000
9.000 1.4564 0.01799 0.01149 -0.1148 0.0044 1.0000
9.250 1.4756 0.01855 0.01211 -0.1134 0.0042 1.0000
9.500 1.4938 0.01915 0.01278 -0.1119 0.0040 1.0000
9.750 1.5110 0.01977 0.01346 -0.1103 0.0038 1.0000
10.000 1.5266 0.02038 0.01413 -0.1083 0.0036 1.0000
10.250 1.5412 0.02100 0.01480 -0.1063 0.0033 1.0000
10.500 1.5538 0.02175 0.01561 -0.1039 0.0032 1.0000
10.750 1.5648 0.02263 0.01656 -0.1014 0.0030 1.0000
11.000 1.5733 0.02372 0.01777 -0.0986 0.0028 1.0000
11.250 1.5845 0.02460 0.01874 -0.0963 0.0028 1.0000
11.500 1.5952 0.02554 0.01977 -0.0941 0.0027 1.0000
11.750 1.6045 0.02661 0.02094 -0.0917 0.0026 1.0000
12.000 1.6131 0.02777 0.02220 -0.0895 0.0025 1.0000
12.250 1.6208 0.02904 0.02357 -0.0872 0.0025 1.0000
12.500 1.6276 0.03042 0.02505 -0.0851 0.0024 1.0000
12.750 1.6341 0.03187 0.02661 -0.0830 0.0023 1.0000
13.000 1.6391 0.03350 0.02836 -0.0810 0.0022 1.0000
13.250 1.6438 0.03522 0.03019 -0.0791 0.0022 1.0000
13.500 1.6481 0.03704 0.03211 -0.0774 0.0021 1.0000
13.750 1.6511 0.03906 0.03425 -0.0758 0.0021 1.0000
14.000 1.6531 0.04124 0.03657 -0.0743 0.0020 1.0000
14.250 1.6539 0.04364 0.03908 -0.0730 0.0020 1.0000
14.500 1.6534 0.04628 0.04185 -0.0719 0.0020 1.0000
14.750 1.6521 0.04911 0.04481 -0.0711 0.0019 1.0000
15.000 1.6485 0.05236 0.04819 -0.0704 0.0019 1.0000
15.250 1.6433 0.05598 0.05194 -0.0701 0.0019 1.0000
15.500 1.6370 0.05994 0.05605 -0.0701 0.0018 1.0000
15.750 1.6280 0.06450 0.06075 -0.0707 0.0018 1.0000
16.000 1.6167 0.06972 0.06613 -0.0717 0.0018 1.0000
16.250 1.6035 0.07556 0.07214 -0.0734 0.0017 1.0000
16.500 1.5897 0.08181 0.07855 -0.0755 0.0017 1.0000
16.750 1.5725 0.08906 0.08597 -0.0785 0.0017 1.0000
17.000 1.5555 0.09666 0.09373 -0.0819 0.0017 1.0000
17.250 1.5348 0.10540 0.10265 -0.0863 0.0017 1.0000
17.500 1.5155 0.11428 0.11169 -0.0911 0.0017 1.0000
17.750 1.4944 0.12401 0.12159 -0.0966 0.0017 1.0000
18.000 1.4752 0.13364 0.13137 -0.1022 0.0017 1.0000
18.250 1.4532 0.14435 0.14223 -0.1087 0.0018 1.0000
18.500 1.4313 0.15542 0.15346 -0.1155 0.0018 1.0000
18.750 1.4066 0.16762 0.16581 -0.1231 0.0018 1.0000
19.000 1.3825 0.17991 0.17823 -0.1310 0.0019 1.0000
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Polar data table (+)
Polar graphs
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