GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 200,000 Max Cl/Cd: 78.98 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe358-il-200000-n5.txt Download as CSV file: xf-goe358-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3690 0.09271 0.08908 -0.0407 1.0000 0.0266
-9.250 -0.3773 0.08932 0.08574 -0.0404 1.0000 0.0272
-9.000 -0.5046 0.03201 0.02759 -0.1093 0.9882 0.0297
-8.750 -0.4619 0.02894 0.02419 -0.1176 0.9860 0.0317
-8.500 -0.4266 0.02833 0.02351 -0.1205 0.9831 0.0335
-8.250 -0.3893 0.02616 0.02095 -0.1255 0.9800 0.0366
-8.000 -0.3517 0.02444 0.01889 -0.1296 0.9775 0.0393
-7.750 -0.3151 0.02405 0.01846 -0.1321 0.9754 0.0415
-7.500 -0.2824 0.02317 0.01738 -0.1341 0.9710 0.0445
-7.250 -0.2458 0.02220 0.01605 -0.1368 0.9679 0.0477
-7.000 -0.2092 0.02101 0.01470 -0.1395 0.9657 0.0504
-6.750 -0.1763 0.02040 0.01404 -0.1410 0.9615 0.0530
-6.500 -0.1416 0.01972 0.01320 -0.1429 0.9575 0.0559
-6.250 -0.1038 0.01900 0.01227 -0.1452 0.9548 0.0587
-6.000 -0.0694 0.01845 0.01152 -0.1467 0.9500 0.0605
-5.750 -0.0358 0.01729 0.01031 -0.1483 0.9449 0.0631
-5.500 0.0008 0.01660 0.00957 -0.1502 0.9414 0.0654
-5.250 0.0307 0.01608 0.00899 -0.1506 0.9337 0.0675
-5.000 0.0656 0.01550 0.00832 -0.1520 0.9288 0.0694
-4.750 0.0961 0.01501 0.00776 -0.1525 0.9203 0.0709
-4.500 0.1310 0.01452 0.00716 -0.1537 0.9134 0.0726
-4.250 0.1614 0.01408 0.00666 -0.1540 0.9011 0.0743
-4.000 0.1931 0.01355 0.00610 -0.1546 0.8874 0.0767
-3.750 0.2249 0.01314 0.00562 -0.1552 0.8729 0.0789
-3.500 0.2563 0.01281 0.00522 -0.1556 0.8590 0.0813
-3.250 0.2874 0.01254 0.00485 -0.1560 0.8463 0.0842
-3.000 0.3178 0.01232 0.00452 -0.1563 0.8324 0.0875
-2.750 0.3478 0.01206 0.00422 -0.1565 0.8173 0.0944
-2.500 0.3776 0.01179 0.00395 -0.1567 0.8017 0.1127
-2.250 0.4072 0.01147 0.00370 -0.1570 0.7863 0.1587
-2.000 0.4363 0.01123 0.00360 -0.1572 0.7716 0.2213
-1.750 0.4646 0.01123 0.00361 -0.1570 0.7575 0.2618
-1.500 0.4928 0.01130 0.00361 -0.1568 0.7437 0.2845
-1.250 0.5207 0.01141 0.00362 -0.1565 0.7298 0.3023
-1.000 0.5484 0.01152 0.00365 -0.1562 0.7159 0.3138
-0.750 0.5761 0.01163 0.00367 -0.1558 0.7016 0.3249
-0.500 0.6036 0.01175 0.00371 -0.1555 0.6870 0.3343
-0.250 0.6310 0.01186 0.00377 -0.1552 0.6722 0.3429
0.000 0.6583 0.01202 0.00385 -0.1548 0.6572 0.3558
0.250 0.6853 0.01218 0.00399 -0.1544 0.6413 0.3672
0.500 0.7123 0.01232 0.00407 -0.1540 0.6243 0.3758
0.750 0.7391 0.01244 0.00414 -0.1536 0.6063 0.3824
1.000 0.7658 0.01259 0.00416 -0.1531 0.5876 0.3885
1.250 0.7921 0.01272 0.00424 -0.1527 0.5689 0.3925
1.500 0.8184 0.01287 0.00432 -0.1522 0.5499 0.3966
1.750 0.8444 0.01306 0.00440 -0.1517 0.5301 0.4013
2.000 0.8703 0.01326 0.00451 -0.1512 0.5108 0.4059
2.250 0.8961 0.01346 0.00466 -0.1506 0.4932 0.4099
2.500 0.9221 0.01366 0.00481 -0.1502 0.4779 0.4144
2.750 0.9480 0.01387 0.00496 -0.1497 0.4646 0.4193
3.000 0.9738 0.01408 0.00515 -0.1492 0.4521 0.4236
3.250 0.9997 0.01429 0.00535 -0.1488 0.4400 0.4288
3.500 1.0258 0.01450 0.00556 -0.1483 0.4295 0.4349
3.750 1.0514 0.01474 0.00578 -0.1479 0.4204 0.4401
4.000 1.0776 0.01493 0.00602 -0.1475 0.4117 0.4458
4.250 1.1032 0.01519 0.00627 -0.1470 0.4047 0.4522
4.500 1.1293 0.01538 0.00654 -0.1466 0.3974 0.4581
4.750 1.1545 0.01564 0.00681 -0.1461 0.3895 0.4657
5.000 1.1802 0.01586 0.00711 -0.1456 0.3818 0.4733
5.250 1.2053 0.01612 0.00740 -0.1451 0.3743 0.4819
5.500 1.2306 0.01635 0.00772 -0.1445 0.3675 0.4904
6.000 1.2802 0.01688 0.00837 -0.1433 0.3544 0.5126
6.250 1.3053 0.01708 0.00873 -0.1428 0.3471 0.5279
6.750 1.3532 0.01755 0.00947 -0.1413 0.3294 0.5877
7.000 1.3719 0.01737 0.00976 -0.1394 0.3209 1.0000
7.250 1.3959 0.01768 0.01017 -0.1387 0.3108 1.0000
7.500 1.4185 0.01805 0.01057 -0.1378 0.2985 1.0000
7.750 1.4397 0.01847 0.01099 -0.1366 0.2779 1.0000
8.000 1.4583 0.01905 0.01145 -0.1351 0.2383 1.0000
8.250 1.4672 0.02039 0.01233 -0.1324 0.1770 1.0000
8.500 1.4799 0.02151 0.01332 -0.1302 0.1556 1.0000
8.750 1.4946 0.02243 0.01422 -0.1282 0.1382 1.0000
9.000 1.5086 0.02334 0.01511 -0.1261 0.1161 1.0000
9.250 1.5170 0.02449 0.01611 -0.1232 0.0920 1.0000
9.500 1.5236 0.02567 0.01723 -0.1201 0.0780 1.0000
9.750 1.5313 0.02683 0.01839 -0.1173 0.0691 1.0000
10.000 1.5382 0.02807 0.01965 -0.1144 0.0621 1.0000
10.250 1.5453 0.02934 0.02097 -0.1118 0.0557 1.0000
10.500 1.5526 0.03064 0.02234 -0.1093 0.0500 1.0000
10.750 1.5582 0.03210 0.02386 -0.1069 0.0441 1.0000
11.000 1.5642 0.03361 0.02547 -0.1046 0.0394 1.0000
11.250 1.5681 0.03533 0.02724 -0.1024 0.0351 1.0000
11.500 1.5701 0.03732 0.02929 -0.1002 0.0322 1.0000
11.750 1.5730 0.03932 0.03141 -0.0983 0.0298 1.0000
12.000 1.5737 0.04163 0.03380 -0.0966 0.0278 1.0000
12.250 1.5715 0.04436 0.03661 -0.0951 0.0262 1.0000
12.500 1.5697 0.04719 0.03956 -0.0938 0.0250 1.0000
12.750 1.5683 0.05010 0.04261 -0.0928 0.0239 1.0000
13.000 1.5656 0.05327 0.04592 -0.0921 0.0230 1.0000
13.250 1.5618 0.05666 0.04943 -0.0915 0.0222 1.0000
13.500 1.5562 0.06038 0.05326 -0.0912 0.0214 1.0000
13.750 1.5485 0.06452 0.05753 -0.0911 0.0208 1.0000
14.000 1.5404 0.06883 0.06194 -0.0912 0.0203 1.0000
14.250 1.5359 0.07276 0.06603 -0.0914 0.0197 1.0000
14.500 1.5305 0.07692 0.07033 -0.0917 0.0191 1.0000
14.750 1.5248 0.08118 0.07472 -0.0922 0.0186 1.0000
15.000 1.5189 0.08555 0.07921 -0.0929 0.0181 1.0000
15.250 1.5126 0.09003 0.08381 -0.0936 0.0177 1.0000
15.500 1.5064 0.09457 0.08846 -0.0946 0.0173 1.0000
15.750 1.5001 0.09917 0.09316 -0.0956 0.0170 1.0000
16.000 1.4935 0.10382 0.09790 -0.0967 0.0167 1.0000
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