GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 482 AIRFOIL (goe482-il) Reynolds number: 500,000 Max Cl/Cd: 100.28 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe482-il-500000-n5.txt Download as CSV file: xf-goe482-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 482 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.1498 0.09163 0.08776 -0.1304 0.7356 0.0283
-11.250 0.1418 0.08644 0.08253 -0.1328 0.7317 0.0313
-11.000 0.1539 0.08497 0.08107 -0.1334 0.7260 0.0315
-10.750 0.1666 0.08366 0.07974 -0.1339 0.7202 0.0318
-10.500 0.1780 0.08219 0.07824 -0.1344 0.7150 0.0323
-10.000 0.1722 0.07435 0.07039 -0.1381 0.7046 0.0358
-9.750 0.1826 0.07286 0.06887 -0.1384 0.6985 0.0360
-8.750 0.0169 0.02784 0.02346 -0.1799 0.6782 0.0424
-8.500 0.0387 0.02488 0.02017 -0.1846 0.6706 0.0429
-8.250 0.0628 0.02292 0.01792 -0.1871 0.6631 0.0434
-8.000 0.0886 0.02137 0.01613 -0.1888 0.6545 0.0439
-7.750 0.1148 0.02017 0.01467 -0.1900 0.6461 0.0444
-7.500 0.1420 0.01919 0.01347 -0.1910 0.6375 0.0449
-7.250 0.1690 0.01833 0.01238 -0.1917 0.6290 0.0453
-7.000 0.1966 0.01759 0.01145 -0.1923 0.6195 0.0456
-6.750 0.2239 0.01701 0.01067 -0.1926 0.6103 0.0459
-6.500 0.2515 0.01651 0.01000 -0.1929 0.6004 0.0461
-6.250 0.2789 0.01588 0.00922 -0.1933 0.5922 0.0465
-6.000 0.3063 0.01537 0.00860 -0.1935 0.5835 0.0469
-5.750 0.3338 0.01502 0.00816 -0.1937 0.5757 0.0473
-5.500 0.3616 0.01473 0.00779 -0.1938 0.5677 0.0476
-5.250 0.3890 0.01450 0.00745 -0.1938 0.5608 0.0480
-5.000 0.4171 0.01425 0.00715 -0.1940 0.5544 0.0484
-4.750 0.4448 0.01408 0.00689 -0.1940 0.5479 0.0490
-4.500 0.4725 0.01391 0.00663 -0.1941 0.5423 0.0496
-4.250 0.5007 0.01370 0.00636 -0.1942 0.5367 0.0501
-4.000 0.5284 0.01352 0.00610 -0.1942 0.5312 0.0506
-3.750 0.5559 0.01338 0.00587 -0.1942 0.5261 0.0511
-3.500 0.5842 0.01321 0.00565 -0.1943 0.5215 0.0516
-3.250 0.6121 0.01308 0.00546 -0.1943 0.5167 0.0521
-3.000 0.6396 0.01300 0.00531 -0.1943 0.5119 0.0526
-2.750 0.6672 0.01294 0.00518 -0.1942 0.5079 0.0530
-2.500 0.6956 0.01271 0.00495 -0.1944 0.5040 0.0538
-2.250 0.7236 0.01260 0.00482 -0.1945 0.5001 0.0546
-2.000 0.7511 0.01255 0.00475 -0.1945 0.4963 0.0555
-1.750 0.7782 0.01256 0.00470 -0.1944 0.4923 0.0566
-1.500 0.8061 0.01252 0.00465 -0.1944 0.4890 0.0577
-1.250 0.8340 0.01248 0.00460 -0.1944 0.4854 0.0587
-1.000 0.8615 0.01247 0.00456 -0.1944 0.4820 0.0596
-0.750 0.8885 0.01249 0.00454 -0.1943 0.4784 0.0605
-0.500 0.9152 0.01251 0.00452 -0.1941 0.4749 0.0617
-0.250 0.9427 0.01249 0.00451 -0.1941 0.4717 0.0635
0.000 0.9700 0.01250 0.00452 -0.1940 0.4680 0.0654
0.250 0.9968 0.01254 0.00455 -0.1939 0.4644 0.0678
0.500 1.0230 0.01261 0.00459 -0.1936 0.4609 0.0702
0.750 1.0489 0.01268 0.00464 -0.1933 0.4576 0.0746
1.000 1.0755 0.01272 0.00470 -0.1932 0.4546 0.0805
1.250 1.1022 0.01271 0.00478 -0.1931 0.4511 0.1035
1.500 1.1282 0.01272 0.00489 -0.1929 0.4472 0.1511
1.750 1.1533 0.01278 0.00501 -0.1926 0.4433 0.1835
2.000 1.1778 0.01284 0.00516 -0.1922 0.4397 0.2360
2.250 1.2040 0.01284 0.00535 -0.1921 0.4367 0.3136
2.500 1.2289 0.01294 0.00551 -0.1917 0.4331 0.3467
2.750 1.2529 0.01308 0.00568 -0.1911 0.4294 0.3673
3.000 1.2758 0.01325 0.00585 -0.1903 0.4258 0.3838
3.250 1.2976 0.01342 0.00603 -0.1893 0.4224 0.4011
3.500 1.3204 0.01353 0.00619 -0.1885 0.4187 0.4179
3.750 1.3416 0.01366 0.00638 -0.1874 0.4146 0.4369
4.250 1.3807 0.01406 0.00690 -0.1848 0.4066 0.4983
4.500 1.4028 0.01419 0.00717 -0.1840 0.4032 0.5600
4.750 1.4236 0.01435 0.00745 -0.1830 0.3995 0.6143
5.000 1.4426 0.01451 0.00778 -0.1817 0.3956 0.6883
5.500 1.4791 0.01475 0.00838 -0.1787 0.3886 1.0000
5.750 1.4994 0.01506 0.00869 -0.1777 0.3850 1.0000
6.000 1.5179 0.01542 0.00904 -0.1765 0.3811 1.0000
6.250 1.5348 0.01586 0.00945 -0.1750 0.3771 1.0000
6.500 1.5514 0.01633 0.00990 -0.1736 0.3734 1.0000
6.750 1.5705 0.01672 0.01031 -0.1725 0.3700 1.0000
7.000 1.5882 0.01717 0.01077 -0.1713 0.3663 1.0000
7.250 1.6045 0.01770 0.01129 -0.1700 0.3628 1.0000
7.500 1.6194 0.01832 0.01189 -0.1685 0.3595 1.0000
7.750 1.6359 0.01887 0.01246 -0.1672 0.3567 1.0000
8.000 1.6534 0.01941 0.01302 -0.1662 0.3537 1.0000
8.250 1.6697 0.02001 0.01366 -0.1650 0.3504 1.0000
8.500 1.6838 0.02075 0.01439 -0.1637 0.3467 1.0000
8.750 1.6951 0.02166 0.01529 -0.1620 0.3424 1.0000
9.000 1.7107 0.02237 0.01603 -0.1609 0.3384 1.0000
9.250 1.7235 0.02325 0.01693 -0.1596 0.3329 1.0000
9.500 1.7335 0.02433 0.01800 -0.1580 0.3281 1.0000
9.750 1.7456 0.02532 0.01900 -0.1568 0.3238 1.0000
10.000 1.7582 0.02629 0.02001 -0.1556 0.3187 1.0000
10.250 1.7674 0.02751 0.02124 -0.1541 0.3136 1.0000
10.500 1.7756 0.02883 0.02256 -0.1526 0.3087 1.0000
10.750 1.7872 0.02995 0.02372 -0.1515 0.3036 1.0000
11.000 1.7956 0.03133 0.02511 -0.1502 0.2984 1.0000
11.250 1.8008 0.03299 0.02678 -0.1487 0.2936 1.0000
11.500 1.8125 0.03418 0.02803 -0.1478 0.2891 1.0000
11.750 1.8199 0.03576 0.02964 -0.1466 0.2839 1.0000
12.000 1.8218 0.03785 0.03173 -0.1451 0.2779 1.0000
12.250 1.8307 0.03939 0.03331 -0.1442 0.2721 1.0000
12.500 1.8325 0.04161 0.03555 -0.1429 0.2656 1.0000
12.750 1.8358 0.04377 0.03774 -0.1418 0.2589 1.0000
13.000 1.8353 0.04637 0.04036 -0.1406 0.2506 1.0000
13.250 1.8343 0.04911 0.04312 -0.1396 0.2417 1.0000
13.500 1.8271 0.05261 0.04661 -0.1385 0.2309 1.0000
13.750 1.8170 0.05656 0.05055 -0.1374 0.2186 1.0000
14.000 1.8019 0.06124 0.05521 -0.1365 0.2037 1.0000
14.250 1.7838 0.06646 0.06042 -0.1357 0.1893 1.0000
14.500 1.7624 0.07230 0.06624 -0.1352 0.1747 1.0000
14.750 1.7431 0.07806 0.07199 -0.1350 0.1626 1.0000
15.000 1.7267 0.08358 0.07753 -0.1350 0.1525 1.0000
15.250 1.7136 0.08877 0.08275 -0.1352 0.1429 1.0000
15.500 1.6982 0.09438 0.08837 -0.1355 0.1328 1.0000
15.750 1.6813 0.10034 0.09433 -0.1361 0.1213 1.0000
16.000 1.6556 0.10774 0.10169 -0.1371 0.1030 1.0000
16.250 1.6266 0.11580 0.10967 -0.1385 0.0809 1.0000
16.500 1.5987 0.12386 0.11767 -0.1402 0.0581 1.0000
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