GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 482 AIRFOIL (goe482-il) Reynolds number: 500,000 Max Cl/Cd: 107.28 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe482-il-500000.txt Download as CSV file: xf-goe482-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2069 0.09426 0.09070 -0.1334 0.7824 0.0425
-10.750 0.2181 0.09249 0.08888 -0.1340 0.7771 0.0437
-10.500 0.1926 0.08808 0.08451 -0.1386 0.7723 0.0467
-10.250 0.2074 0.08545 0.08188 -0.1382 0.7672 0.0471
-10.000 0.2256 0.08381 0.08018 -0.1378 0.7622 0.0475
-9.750 0.2409 0.08236 0.07872 -0.1377 0.7572 0.0482
-9.500 0.2521 0.08071 0.07707 -0.1379 0.7514 0.0494
-9.250 0.2308 0.07689 0.07325 -0.1422 0.7460 0.0529
-9.000 0.2346 0.07344 0.06978 -0.1427 0.7408 0.0534
-8.750 0.2511 0.07205 0.06839 -0.1419 0.7344 0.0538
-8.500 0.2656 0.07066 0.06696 -0.1416 0.7282 0.0543
-8.250 0.2776 0.06914 0.06543 -0.1415 0.7220 0.0549
-8.000 0.2875 0.06751 0.06380 -0.1415 0.7151 0.0560
-7.750 0.2935 0.06562 0.06187 -0.1419 0.7084 0.0576
-7.500 0.2493 0.05945 0.05578 -0.1459 0.7018 0.0606
-7.250 0.2625 0.05811 0.05441 -0.1448 0.6940 0.0610
-7.000 0.2760 0.05695 0.05323 -0.1442 0.6862 0.0615
-6.750 0.2877 0.05558 0.05183 -0.1440 0.6774 0.0620
-6.500 0.2729 0.04132 0.03743 -0.1690 0.6712 0.0690
-6.250 0.2903 0.04077 0.03691 -0.1670 0.6619 0.0694
-6.000 0.3085 0.04050 0.03659 -0.1656 0.6533 0.0698
-5.750 0.3323 0.02100 0.01547 -0.1909 0.6469 0.0610
-5.500 0.3596 0.01980 0.01397 -0.1917 0.6379 0.0608
-5.250 0.3871 0.01848 0.01244 -0.1925 0.6284 0.0610
-5.000 0.4141 0.01750 0.01130 -0.1930 0.6197 0.0616
-4.750 0.4419 0.01673 0.01039 -0.1933 0.6109 0.0620
-4.500 0.4694 0.01610 0.00959 -0.1935 0.6028 0.0623
-4.250 0.4973 0.01554 0.00890 -0.1937 0.5946 0.0626
-4.000 0.5247 0.01513 0.00834 -0.1938 0.5874 0.0631
-3.750 0.5529 0.01469 0.00783 -0.1939 0.5803 0.0637
-3.500 0.5804 0.01436 0.00738 -0.1940 0.5735 0.0643
-3.250 0.6083 0.01407 0.00699 -0.1940 0.5677 0.0649
-3.000 0.6363 0.01382 0.00668 -0.1941 0.5616 0.0659
-2.750 0.6639 0.01365 0.00640 -0.1940 0.5561 0.0668
-2.500 0.6917 0.01347 0.00615 -0.1940 0.5510 0.0675
-2.250 0.7198 0.01330 0.00593 -0.1940 0.5459 0.0681
-2.000 0.7475 0.01317 0.00573 -0.1940 0.5412 0.0687
-1.750 0.7750 0.01283 0.00532 -0.1941 0.5365 0.0700
-1.500 0.8031 0.01264 0.00515 -0.1942 0.5324 0.0714
-1.250 0.8310 0.01253 0.00504 -0.1942 0.5279 0.0728
-1.000 0.8586 0.01250 0.00497 -0.1942 0.5236 0.0747
-0.750 0.8859 0.01254 0.00494 -0.1941 0.5194 0.0766
-0.500 0.9138 0.01252 0.00490 -0.1941 0.5158 0.0780
-0.250 0.9418 0.01238 0.00478 -0.1943 0.5120 0.0810
0.000 0.9693 0.01236 0.00475 -0.1942 0.5079 0.0843
0.250 0.9963 0.01242 0.00475 -0.1941 0.5038 0.0882
0.500 1.0238 0.01246 0.00479 -0.1941 0.4999 0.0969
0.750 1.0514 0.01234 0.00485 -0.1942 0.4964 0.1404
1.000 1.0789 0.01220 0.00494 -0.1944 0.4927 0.2235
1.250 1.1057 0.01217 0.00512 -0.1944 0.4890 0.3276
1.500 1.1318 0.01235 0.00529 -0.1942 0.4852 0.3652
1.750 1.1581 0.01246 0.00544 -0.1939 0.4816 0.3887
2.000 1.1840 0.01252 0.00556 -0.1936 0.4779 0.4099
2.250 1.2096 0.01261 0.00567 -0.1933 0.4739 0.4277
2.500 1.2348 0.01274 0.00580 -0.1929 0.4702 0.4458
2.750 1.2603 0.01293 0.00599 -0.1926 0.4662 0.4672
3.000 1.2852 0.01296 0.00615 -0.1922 0.4630 0.4967
3.250 1.3099 0.01301 0.00635 -0.1918 0.4592 0.5521
3.500 1.3339 0.01306 0.00655 -0.1912 0.4555 0.6254
3.750 1.3549 0.01298 0.00680 -0.1900 0.4518 0.7816
4.000 1.3777 0.01293 0.00694 -0.1891 0.4480 1.0000
4.250 1.4010 0.01309 0.00710 -0.1884 0.4442 1.0000
4.500 1.4236 0.01327 0.00726 -0.1876 0.4401 1.0000
4.750 1.4445 0.01351 0.00744 -0.1865 0.4361 1.0000
5.000 1.4655 0.01381 0.00768 -0.1854 0.4322 1.0000
5.250 1.4855 0.01400 0.00789 -0.1841 0.4287 1.0000
5.500 1.5053 0.01422 0.00812 -0.1829 0.4248 1.0000
5.750 1.5243 0.01450 0.00837 -0.1815 0.4210 1.0000
6.000 1.5431 0.01486 0.00867 -0.1802 0.4171 1.0000
6.250 1.5623 0.01514 0.00898 -0.1789 0.4136 1.0000
6.500 1.5811 0.01543 0.00929 -0.1776 0.4097 1.0000
6.750 1.5989 0.01577 0.00963 -0.1762 0.4057 1.0000
7.000 1.6159 0.01620 0.01001 -0.1747 0.4018 1.0000
7.250 1.6337 0.01661 0.01043 -0.1734 0.3981 1.0000
7.500 1.6513 0.01699 0.01084 -0.1721 0.3945 1.0000
7.750 1.6685 0.01742 0.01129 -0.1708 0.3909 1.0000
8.000 1.6846 0.01792 0.01177 -0.1693 0.3873 1.0000
8.250 1.7015 0.01849 0.01229 -0.1681 0.3834 1.0000
8.500 1.7171 0.01898 0.01286 -0.1666 0.3802 1.0000
8.750 1.7313 0.01955 0.01346 -0.1651 0.3756 1.0000
9.000 1.7436 0.02026 0.01415 -0.1634 0.3707 1.0000
9.250 1.7562 0.02102 0.01490 -0.1618 0.3659 1.0000
9.500 1.7700 0.02170 0.01565 -0.1604 0.3617 1.0000
9.750 1.7827 0.02249 0.01646 -0.1589 0.3573 1.0000
10.000 1.7933 0.02345 0.01738 -0.1573 0.3527 1.0000
10.250 1.8057 0.02432 0.01831 -0.1560 0.3485 1.0000
10.500 1.8183 0.02521 0.01925 -0.1547 0.3441 1.0000
10.750 1.8279 0.02630 0.02035 -0.1532 0.3394 1.0000
11.000 1.8370 0.02747 0.02150 -0.1517 0.3350 1.0000
11.250 1.8498 0.02843 0.02256 -0.1506 0.3315 1.0000
11.500 1.8594 0.02962 0.02379 -0.1493 0.3267 1.0000
11.750 1.8666 0.03101 0.02517 -0.1478 0.3221 1.0000
12.000 1.8751 0.03236 0.02656 -0.1465 0.3180 1.0000
12.250 1.8857 0.03358 0.02787 -0.1455 0.3138 1.0000
12.500 1.8924 0.03514 0.02946 -0.1442 0.3091 1.0000
12.750 1.8959 0.03698 0.03129 -0.1428 0.3043 1.0000
13.000 1.9046 0.03850 0.03290 -0.1418 0.2994 1.0000
13.250 1.9077 0.04052 0.03496 -0.1406 0.2931 1.0000
13.500 1.9083 0.04282 0.03728 -0.1393 0.2868 1.0000
13.750 1.9126 0.04490 0.03943 -0.1384 0.2801 1.0000
14.000 1.9084 0.04785 0.04237 -0.1371 0.2732 1.0000
14.250 1.9107 0.05027 0.04487 -0.1363 0.2650 1.0000
14.500 1.9039 0.05371 0.04832 -0.1353 0.2561 1.0000
14.750 1.8928 0.05777 0.05239 -0.1343 0.2442 1.0000
15.000 1.8805 0.06213 0.05675 -0.1335 0.2309 1.0000
15.250 1.8619 0.06739 0.06199 -0.1329 0.2159 1.0000
15.500 1.8388 0.07342 0.06799 -0.1324 0.2004 1.0000
15.750 1.8135 0.07994 0.07450 -0.1323 0.1847 1.0000
16.000 1.7877 0.08674 0.08127 -0.1324 0.1705 1.0000
16.250 1.7632 0.09353 0.08805 -0.1329 0.1575 1.0000
16.500 1.7395 0.10038 0.09490 -0.1335 0.1448 1.0000
16.750 1.7170 0.10722 0.10173 -0.1345 0.1310 1.0000
17.000 1.6922 0.11453 0.10899 -0.1358 0.1142 1.0000
17.250 1.6629 0.12270 0.11708 -0.1375 0.0937 1.0000
17.500 1.6334 0.13102 0.12532 -0.1397 0.0709 1.0000
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