GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 500,000 Max Cl/Cd: 102.6 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe366-il-500000.txt Download as CSV file: xf-goe366-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 366 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
------ -------- --------- --------- -------- -------- --------
-9.750 0.0234 0.09914 0.09648 -0.0941 0.9097 0.0214
-9.500 0.0310 0.09663 0.09393 -0.0952 0.8991 0.0218
-9.250 0.0380 0.09415 0.09142 -0.0968 0.8886 0.0220
-9.000 0.1076 0.07833 0.07551 -0.1032 0.8426 0.0222
-8.750 0.1205 0.07511 0.07229 -0.1024 0.8346 0.0223
-8.500 0.1291 0.07236 0.06949 -0.1024 0.8277 0.0224
-8.250 0.1371 0.06968 0.06681 -0.1028 0.8204 0.0225
-8.000 0.1445 0.06707 0.06417 -0.1033 0.8135 0.0226
-7.750 0.1517 0.06447 0.06154 -0.1041 0.8073 0.0228
-7.500 0.1588 0.06186 0.05892 -0.1049 0.8004 0.0230
-7.250 0.1658 0.05928 0.05629 -0.1058 0.7944 0.0233
-7.000 0.1728 0.05667 0.05367 -0.1069 0.7884 0.0236
-6.750 0.1795 0.05403 0.05103 -0.1081 0.7823 0.0239
-6.500 0.1852 0.05145 0.04840 -0.1094 0.7767 0.0242
-6.250 0.1939 0.04861 0.04556 -0.1119 0.7711 0.0245
-6.000 0.2067 0.04536 0.04228 -0.1163 0.7656 0.0250
-5.750 0.2277 0.04096 0.03775 -0.1262 0.7607 0.0253
-5.500 0.2495 0.03689 0.03357 -0.1321 0.7560 0.0254
-5.250 0.2610 0.03432 0.03102 -0.1314 0.7502 0.0255
-5.000 0.2768 0.03194 0.02860 -0.1321 0.7449 0.0256
-4.750 0.2946 0.02962 0.02621 -0.1332 0.7397 0.0258
-4.500 0.3142 0.02726 0.02382 -0.1349 0.7338 0.0261
-4.250 0.3358 0.02492 0.02140 -0.1369 0.7283 0.0265
-4.000 0.3664 0.03884 0.03501 -0.1473 0.7359 0.0266
-3.750 0.3925 0.03670 0.03276 -0.1490 0.7299 0.0272
-3.500 0.4210 0.03450 0.03038 -0.1508 0.7242 0.0281
-3.250 0.4602 0.03121 0.02668 -0.1532 0.7187 0.0289
-3.000 0.4814 0.02935 0.02482 -0.1536 0.7120 0.0291
-2.750 0.5050 0.02792 0.02330 -0.1541 0.7056 0.0294
-2.500 0.5296 0.02651 0.02184 -0.1545 0.6986 0.0299
-2.250 0.5560 0.02511 0.02030 -0.1548 0.6914 0.0307
-2.000 0.5895 0.02314 0.01784 -0.1548 0.6845 0.0330
-1.750 0.6132 0.02170 0.01640 -0.1550 0.6755 0.0333
-1.500 0.6383 0.02069 0.01532 -0.1551 0.6665 0.0339
-1.250 0.6642 0.01975 0.01425 -0.1550 0.6562 0.0350
-1.000 0.6930 0.01860 0.01276 -0.1545 0.6449 0.0378
-0.750 0.7175 0.01775 0.01186 -0.1544 0.6309 0.0386
-0.500 0.7425 0.01711 0.01107 -0.1539 0.6136 0.0402
-0.250 0.7680 0.01641 0.01005 -0.1531 0.5940 0.0433
0.000 0.7911 0.01592 0.00943 -0.1524 0.5744 0.0447
0.250 0.8155 0.01559 0.00882 -0.1515 0.5573 0.0494
0.500 0.8390 0.01521 0.00836 -0.1510 0.5426 0.0518
0.750 0.8634 0.01492 0.00791 -0.1504 0.5301 0.0579
1.000 0.8872 0.01474 0.00758 -0.1497 0.5190 0.0659
1.250 0.9122 0.01449 0.00728 -0.1494 0.5092 0.0761
1.500 0.9363 0.01427 0.00700 -0.1489 0.5007 0.0891
2.250 1.0148 0.01367 0.00598 -0.1466 0.4784 0.0636
2.500 1.0403 0.01322 0.00544 -0.1458 0.4714 0.0477
2.750 1.0652 0.01302 0.00522 -0.1453 0.4651 0.0445
3.000 1.0907 0.01301 0.00518 -0.1448 0.4587 0.0429
3.250 1.1149 0.01306 0.00519 -0.1442 0.4527 0.0427
3.500 1.1400 0.01306 0.00520 -0.1438 0.4471 0.0431
3.750 1.1650 0.01309 0.00524 -0.1434 0.4412 0.0445
4.000 1.1885 0.01323 0.00535 -0.1427 0.4354 0.0467
4.250 1.2127 0.01337 0.00547 -0.1421 0.4300 0.0477
4.500 1.2370 0.01348 0.00558 -0.1415 0.4246 0.0497
4.750 1.2599 0.01367 0.00574 -0.1408 0.4196 0.0549
5.000 1.2796 0.01253 0.00625 -0.1397 0.4150 1.0000
5.250 1.3030 0.01270 0.00642 -0.1389 0.4104 1.0000
5.500 1.3244 0.01294 0.00660 -0.1379 0.4052 1.0000
5.750 1.3444 0.01327 0.00685 -0.1366 0.3998 1.0000
6.000 1.3665 0.01349 0.00708 -0.1357 0.3950 1.0000
6.250 1.3882 0.01374 0.00732 -0.1348 0.3902 1.0000
6.500 1.4088 0.01405 0.00760 -0.1337 0.3858 1.0000
6.750 1.4292 0.01442 0.00792 -0.1326 0.3813 1.0000
7.000 1.4508 0.01465 0.00821 -0.1318 0.3770 1.0000
7.250 1.4713 0.01496 0.00851 -0.1307 0.3724 1.0000
7.500 1.4904 0.01535 0.00886 -0.1295 0.3678 1.0000
7.750 1.5106 0.01571 0.00924 -0.1285 0.3637 1.0000
8.000 1.5314 0.01602 0.00959 -0.1276 0.3599 1.0000
8.250 1.5513 0.01638 0.00996 -0.1266 0.3561 1.0000
8.500 1.5697 0.01682 0.01039 -0.1254 0.3522 1.0000
8.750 1.5885 0.01728 0.01085 -0.1243 0.3482 1.0000
9.000 1.6083 0.01764 0.01128 -0.1233 0.3446 1.0000
9.250 1.6268 0.01806 0.01173 -0.1222 0.3404 1.0000
9.500 1.6434 0.01860 0.01225 -0.1209 0.3359 1.0000
9.750 1.6603 0.01913 0.01282 -0.1196 0.3313 1.0000
10.000 1.6780 0.01960 0.01335 -0.1186 0.3260 1.0000
10.250 1.6932 0.02022 0.01397 -0.1171 0.3208 1.0000
10.500 1.7083 0.02089 0.01464 -0.1158 0.3162 1.0000
10.750 1.7257 0.02142 0.01527 -0.1148 0.3115 1.0000
11.000 1.7409 0.02210 0.01597 -0.1135 0.3065 1.0000
11.500 1.7698 0.02357 0.01752 -0.1109 0.2964 1.0000
11.750 1.7822 0.02445 0.01843 -0.1095 0.2900 1.0000
12.000 1.7941 0.02540 0.01940 -0.1080 0.2841 1.0000
12.250 1.8079 0.02624 0.02031 -0.1069 0.2779 1.0000
12.500 1.8173 0.02739 0.02146 -0.1053 0.2720 1.0000
12.750 1.8301 0.02834 0.02249 -0.1041 0.2658 1.0000
13.000 1.8377 0.02969 0.02384 -0.1026 0.2577 1.0000
13.250 1.8471 0.03095 0.02515 -0.1012 0.2487 1.0000
13.500 1.8518 0.03261 0.02682 -0.0996 0.2391 1.0000
13.750 1.8556 0.03442 0.02862 -0.0980 0.2279 1.0000
14.000 1.8579 0.03641 0.03061 -0.0964 0.2153 1.0000
14.250 1.8559 0.03884 0.03302 -0.0946 0.2010 1.0000
14.500 1.8488 0.04181 0.03594 -0.0927 0.1852 1.0000
14.750 1.8391 0.04512 0.03921 -0.0908 0.1685 1.0000
15.000 1.8271 0.04880 0.04285 -0.0890 0.1537 1.0000
15.250 1.8150 0.05261 0.04665 -0.0875 0.1426 1.0000
15.500 1.8032 0.05652 0.05057 -0.0862 0.1339 1.0000
15.750 1.7948 0.06019 0.05428 -0.0852 0.1276 1.0000
16.000 1.7822 0.06446 0.05859 -0.0843 0.1215 1.0000
16.250 1.7739 0.06832 0.06253 -0.0838 0.1166 1.0000
16.500 1.7641 0.07247 0.06674 -0.0833 0.1121 1.0000
16.750 1.7504 0.07721 0.07154 -0.0831 0.1081 1.0000
17.000 1.7449 0.08096 0.07538 -0.0830 0.1039 1.0000
17.250 1.7336 0.08548 0.07997 -0.0830 0.0996 1.0000
17.500 1.7191 0.09051 0.08506 -0.0832 0.0957 1.0000
17.750 1.7124 0.09452 0.08915 -0.0834 0.0904 1.0000
18.000 1.6966 0.09985 0.09451 -0.0839 0.0851 1.0000
18.250 1.6863 0.10443 0.09915 -0.0845 0.0784 1.0000
18.500 1.6715 0.10969 0.10444 -0.0853 0.0718 1.0000
18.750 1.6544 0.11538 0.11014 -0.0863 0.0638 1.0000
19.000 1.6357 0.12138 0.11613 -0.0876 0.0549 1.0000
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