GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 200,000 Max Cl/Cd: 73.26 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe366-il-200000-n5.txt Download as CSV file: xf-goe366-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0450 0.09700 0.09293 -0.0974 0.8936 0.0279
-9.000 0.0533 0.09450 0.09041 -0.0985 0.8835 0.0283
-8.750 0.0613 0.09205 0.08793 -0.0997 0.8741 0.0286
-8.500 0.0688 0.08962 0.08547 -0.1012 0.8649 0.0289
-8.250 0.0741 0.08733 0.08316 -0.1036 0.8550 0.0291
-8.000 0.0807 0.08486 0.08066 -0.1055 0.8458 0.0292
-7.750 0.0918 0.08220 0.07799 -0.1052 0.8370 0.0294
-7.500 0.1015 0.07976 0.07551 -0.1057 0.8285 0.0296
-7.250 0.1103 0.07743 0.07318 -0.1065 0.8195 0.0299
-7.000 0.1185 0.07518 0.07089 -0.1076 0.8118 0.0301
-6.750 0.1282 0.07285 0.06856 -0.1094 0.8041 0.0305
-6.500 0.1407 0.07032 0.06600 -0.1119 0.7969 0.0309
-6.250 0.1549 0.06770 0.06334 -0.1149 0.7903 0.0313
-6.000 0.1708 0.06498 0.06058 -0.1185 0.7831 0.0319
-5.750 0.1914 0.06191 0.05740 -0.1239 0.7769 0.0324
-5.250 0.2316 0.05612 0.05148 -0.1310 0.7637 0.0330
-5.000 0.2492 0.05389 0.04919 -0.1319 0.7580 0.0335
-4.750 0.2694 0.05159 0.04684 -0.1339 0.7512 0.0343
-4.500 0.2932 0.04908 0.04422 -0.1366 0.7449 0.0352
-4.250 0.3237 0.04620 0.04113 -0.1409 0.7389 0.0363
-4.000 0.3522 0.04339 0.03813 -0.1440 0.7320 0.0368
-3.750 0.3718 0.04143 0.03612 -0.1443 0.7256 0.0372
-3.500 0.3944 0.03956 0.03418 -0.1452 0.7189 0.0379
-3.250 0.4197 0.03763 0.03213 -0.1464 0.7115 0.0391
-3.000 0.4549 0.03520 0.02927 -0.1487 0.7052 0.0411
-2.750 0.4751 0.03354 0.02764 -0.1488 0.6971 0.0417
-2.500 0.4994 0.03209 0.02608 -0.1492 0.6892 0.0432
-2.250 0.5281 0.03035 0.02409 -0.1499 0.6813 0.0465
-2.000 0.5518 0.02911 0.02277 -0.1500 0.6721 0.0484
-1.750 0.5802 0.02764 0.02103 -0.1503 0.6631 0.0520
-1.500 0.6043 0.02650 0.01981 -0.1502 0.6525 0.0540
-1.250 0.6312 0.02535 0.01842 -0.1501 0.6412 0.0586
-0.750 0.6814 0.02345 0.01620 -0.1497 0.6155 0.0672
-0.500 0.7068 0.02269 0.01521 -0.1493 0.6002 0.0749
0.000 0.7614 0.02040 0.01219 -0.1474 0.5707 0.0503
0.250 0.7831 0.02038 0.01216 -0.1472 0.5568 0.0704
0.500 0.8125 0.01892 0.01010 -0.1456 0.5457 0.0405
0.750 0.8366 0.01844 0.00946 -0.1449 0.5342 0.0392
1.000 0.8617 0.01803 0.00882 -0.1441 0.5238 0.0376
1.250 0.8862 0.01787 0.00839 -0.1432 0.5147 0.0365
1.500 0.9110 0.01759 0.00805 -0.1426 0.5062 0.0363
1.750 0.9353 0.01742 0.00778 -0.1419 0.4984 0.0362
2.000 0.9600 0.01728 0.00757 -0.1413 0.4910 0.0363
2.250 0.9841 0.01715 0.00743 -0.1407 0.4834 0.0374
2.500 1.0081 0.01711 0.00736 -0.1401 0.4767 0.0387
2.750 1.0326 0.01706 0.00731 -0.1396 0.4698 0.0391
3.000 1.0566 0.01709 0.00731 -0.1390 0.4637 0.0393
3.250 1.0809 0.01714 0.00734 -0.1385 0.4581 0.0398
3.500 1.1051 0.01721 0.00740 -0.1379 0.4519 0.0404
3.750 1.1286 0.01735 0.00749 -0.1373 0.4460 0.0412
4.000 1.1521 0.01751 0.00761 -0.1366 0.4406 0.0438
4.250 1.1756 0.01767 0.00776 -0.1360 0.4350 0.0461
4.500 1.1986 0.01787 0.00794 -0.1352 0.4298 0.0483
4.750 1.2211 0.01813 0.00814 -0.1344 0.4253 0.0518
5.250 1.2623 0.01723 0.00883 -0.1320 0.4156 1.0000
5.500 1.2829 0.01756 0.00908 -0.1309 0.4108 1.0000
5.750 1.3036 0.01792 0.00935 -0.1298 0.4065 1.0000
6.000 1.3247 0.01822 0.00967 -0.1288 0.4019 1.0000
6.250 1.3455 0.01857 0.01000 -0.1278 0.3976 1.0000
6.500 1.3658 0.01894 0.01034 -0.1267 0.3936 1.0000
6.750 1.3863 0.01936 0.01069 -0.1257 0.3900 1.0000
7.000 1.4067 0.01971 0.01110 -0.1247 0.3857 1.0000
7.250 1.4260 0.02011 0.01152 -0.1235 0.3811 1.0000
7.500 1.4445 0.02054 0.01193 -0.1223 0.3766 1.0000
7.750 1.4632 0.02101 0.01237 -0.1211 0.3725 1.0000
8.000 1.4813 0.02145 0.01288 -0.1198 0.3676 1.0000
8.250 1.4987 0.02193 0.01338 -0.1185 0.3629 1.0000
8.500 1.5161 0.02244 0.01390 -0.1172 0.3588 1.0000
8.750 1.5340 0.02297 0.01443 -0.1160 0.3552 1.0000
9.000 1.5516 0.02349 0.01503 -0.1148 0.3511 1.0000
9.250 1.5685 0.02404 0.01566 -0.1136 0.3472 1.0000
9.500 1.5846 0.02464 0.01628 -0.1123 0.3433 1.0000
9.750 1.6006 0.02527 0.01688 -0.1110 0.3395 1.0000
10.000 1.6154 0.02593 0.01767 -0.1096 0.3349 1.0000
10.250 1.6300 0.02663 0.01844 -0.1082 0.3305 1.0000
10.500 1.6440 0.02737 0.01921 -0.1067 0.3265 1.0000
10.750 1.6585 0.02811 0.01996 -0.1054 0.3229 1.0000
11.000 1.6717 0.02893 0.02093 -0.1040 0.3185 1.0000
11.250 1.6834 0.02982 0.02190 -0.1025 0.3135 1.0000
11.500 1.6935 0.03081 0.02290 -0.1008 0.3085 1.0000
11.750 1.7038 0.03184 0.02403 -0.0993 0.3031 1.0000
12.000 1.7127 0.03298 0.02527 -0.0978 0.2970 1.0000
12.250 1.7197 0.03425 0.02654 -0.0960 0.2915 1.0000
12.500 1.7279 0.03553 0.02796 -0.0946 0.2852 1.0000
12.750 1.7343 0.03695 0.02945 -0.0931 0.2791 1.0000
13.000 1.7403 0.03846 0.03101 -0.0916 0.2735 1.0000
13.250 1.7456 0.04009 0.03277 -0.0902 0.2663 1.0000
13.500 1.7472 0.04206 0.03475 -0.0886 0.2590 1.0000
13.750 1.7499 0.04405 0.03687 -0.0873 0.2499 1.0000
14.000 1.7499 0.04636 0.03922 -0.0860 0.2413 1.0000
14.250 1.7491 0.04882 0.04174 -0.0848 0.2318 1.0000
14.500 1.7475 0.05143 0.04442 -0.0836 0.2221 1.0000
14.750 1.7423 0.05451 0.04753 -0.0825 0.2118 1.0000
15.000 1.7340 0.05802 0.05108 -0.0814 0.2005 1.0000
15.250 1.7245 0.06180 0.05489 -0.0806 0.1883 1.0000
15.500 1.7118 0.06607 0.05919 -0.0799 0.1764 1.0000
15.750 1.6975 0.07070 0.06384 -0.0794 0.1654 1.0000
16.000 1.6813 0.07572 0.06889 -0.0791 0.1559 1.0000
16.250 1.6652 0.08086 0.07408 -0.0791 0.1479 1.0000
16.500 1.6509 0.08586 0.07914 -0.0793 0.1410 1.0000
16.750 1.6348 0.09120 0.08452 -0.0796 0.1350 1.0000
17.000 1.6225 0.09608 0.08948 -0.0801 0.1299 1.0000
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