GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Reynolds number: 200,000 Max Cl/Cd: 80.37 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe198-il-200000-n5.txt Download as CSV file: xf-goe198-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 198 (L.F.G. 5294) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1451 0.09222 0.08847 -0.0614 0.9338 0.0300
-7.750 -0.1348 0.08959 0.08582 -0.0631 0.9276 0.0307
-7.500 -0.1263 0.08718 0.08341 -0.0648 0.9205 0.0319
-7.250 -0.1134 0.08492 0.08111 -0.0703 0.9138 0.0330
-7.000 -0.0963 0.08227 0.07843 -0.0769 0.9066 0.0331
-6.750 -0.0754 0.07924 0.07533 -0.0836 0.9007 0.0332
-6.500 -0.0647 0.07576 0.07184 -0.0823 0.8968 0.0335
-6.250 -0.0523 0.07284 0.06893 -0.0819 0.8914 0.0338
-6.000 -0.0364 0.07017 0.06624 -0.0833 0.8860 0.0343
-5.750 -0.0178 0.06754 0.06357 -0.0857 0.8812 0.0350
-5.500 0.0031 0.06493 0.06094 -0.0888 0.8752 0.0362
-5.250 0.0317 0.06208 0.05802 -0.0946 0.8703 0.0386
-5.000 0.0796 0.05865 0.05435 -0.1066 0.8662 0.0394
-4.750 0.1035 0.05535 0.05103 -0.1095 0.8609 0.0396
-4.500 0.1195 0.05270 0.04840 -0.1092 0.8561 0.0400
-4.250 0.1412 0.05031 0.04596 -0.1104 0.8518 0.0407
-4.000 0.1673 0.04798 0.04359 -0.1127 0.8457 0.0417
-3.750 0.1972 0.04556 0.04108 -0.1158 0.8397 0.0432
-3.500 0.2505 0.04226 0.03743 -0.1243 0.8349 0.0465
-3.250 0.2711 0.03998 0.03518 -0.1248 0.8276 0.0471
-3.000 0.2975 0.03796 0.03309 -0.1261 0.8218 0.0480
-2.750 0.3274 0.03599 0.03104 -0.1280 0.8150 0.0493
-2.500 0.3610 0.03395 0.02886 -0.1304 0.8078 0.0515
-2.250 0.4101 0.03168 0.02603 -0.1347 0.8022 0.0537
-1.500 0.5082 0.02326 0.01697 -0.1396 0.7797 0.0392
-1.250 0.5381 0.02185 0.01540 -0.1404 0.7713 0.0385
-1.000 0.5693 0.02038 0.01372 -0.1412 0.7610 0.0378
-0.750 0.6010 0.01892 0.01198 -0.1419 0.7518 0.0373
-0.500 0.6321 0.01760 0.01036 -0.1423 0.7412 0.0371
-0.250 0.6625 0.01648 0.00896 -0.1426 0.7289 0.0372
0.000 0.6920 0.01559 0.00779 -0.1426 0.7153 0.0378
0.250 0.7207 0.01496 0.00688 -0.1425 0.6990 0.0393
0.500 0.7487 0.01444 0.00622 -0.1424 0.6811 0.0402
0.750 0.7765 0.01406 0.00572 -0.1422 0.6639 0.0408
1.000 0.8041 0.01379 0.00535 -0.1420 0.6467 0.0416
1.250 0.8312 0.01361 0.00506 -0.1417 0.6268 0.0427
1.500 0.8581 0.01351 0.00484 -0.1414 0.6046 0.0441
1.750 0.8847 0.01349 0.00469 -0.1411 0.5838 0.0458
2.000 0.9110 0.01359 0.00472 -0.1408 0.5649 0.0495
2.250 0.9375 0.01370 0.00474 -0.1406 0.5485 0.0542
2.500 0.9638 0.01384 0.00480 -0.1402 0.5313 0.0611
2.750 0.9897 0.01399 0.00489 -0.1399 0.5134 0.0756
3.000 1.0157 0.01414 0.00498 -0.1396 0.4963 0.0950
3.250 1.0417 0.01425 0.00515 -0.1393 0.4786 0.1356
4.250 1.1340 0.01411 0.00592 -0.1358 0.3878 1.0000
4.500 1.1571 0.01458 0.00620 -0.1351 0.3661 1.0000
5.000 1.2043 0.01542 0.00686 -0.1338 0.3385 1.0000
5.250 1.2275 0.01587 0.00722 -0.1331 0.3256 1.0000
5.500 1.2501 0.01635 0.00761 -0.1324 0.3125 1.0000
5.750 1.2724 0.01684 0.00802 -0.1315 0.3000 1.0000
6.000 1.2955 0.01724 0.00841 -0.1309 0.2871 1.0000
6.250 1.3185 0.01764 0.00880 -0.1301 0.2753 1.0000
6.500 1.3410 0.01806 0.00920 -0.1294 0.2642 1.0000
6.750 1.3632 0.01848 0.00963 -0.1285 0.2520 1.0000
7.000 1.3853 0.01890 0.01005 -0.1277 0.2383 1.0000
7.250 1.4047 0.01949 0.01055 -0.1265 0.2118 1.0000
7.500 1.4201 0.02037 0.01121 -0.1247 0.1764 1.0000
7.750 1.4337 0.02138 0.01205 -0.1227 0.1459 1.0000
8.250 1.4495 0.02402 0.01425 -0.1170 0.0773 1.0000
8.500 1.4620 0.02484 0.01510 -0.1147 0.0734 1.0000
8.750 1.4750 0.02567 0.01598 -0.1126 0.0713 1.0000
9.000 1.4871 0.02660 0.01699 -0.1105 0.0691 1.0000
9.250 1.4978 0.02765 0.01811 -0.1083 0.0668 1.0000
9.500 1.5071 0.02885 0.01937 -0.1061 0.0646 1.0000
9.750 1.5172 0.03001 0.02063 -0.1041 0.0630 1.0000
10.000 1.5275 0.03118 0.02191 -0.1022 0.0613 1.0000
10.250 1.5362 0.03252 0.02337 -0.1003 0.0596 1.0000
10.500 1.5429 0.03404 0.02500 -0.0983 0.0578 1.0000
10.750 1.5474 0.03579 0.02684 -0.0963 0.0564 1.0000
11.000 1.5496 0.03780 0.02894 -0.0942 0.0551 1.0000
11.250 1.5512 0.03991 0.03114 -0.0922 0.0540 1.0000
11.500 1.5601 0.04141 0.03279 -0.0908 0.0528 1.0000
11.750 1.5672 0.04313 0.03466 -0.0895 0.0509 1.0000
12.000 1.5718 0.04512 0.03676 -0.0881 0.0491 1.0000
12.250 1.5739 0.04741 0.03916 -0.0867 0.0474 1.0000
12.500 1.5714 0.05025 0.04208 -0.0853 0.0460 1.0000
12.750 1.5777 0.05225 0.04423 -0.0844 0.0442 1.0000
13.000 1.5847 0.05421 0.04638 -0.0836 0.0418 1.0000
13.250 1.5891 0.05652 0.04881 -0.0830 0.0394 1.0000
13.500 1.5950 0.05874 0.05118 -0.0824 0.0365 1.0000
13.750 1.6025 0.06082 0.05339 -0.0820 0.0326 1.0000
14.000 1.6074 0.06327 0.05597 -0.0816 0.0283 1.0000
14.250 1.6093 0.06616 0.05894 -0.0814 0.0252 1.0000
14.500 1.6091 0.06943 0.06225 -0.0814 0.0231 1.0000
14.750 1.6056 0.07323 0.06613 -0.0815 0.0218 1.0000
15.000 1.6003 0.07738 0.07037 -0.0818 0.0208 1.0000
15.250 1.5935 0.08182 0.07491 -0.0823 0.0200 1.0000
15.500 1.5856 0.08651 0.07969 -0.0829 0.0193 1.0000
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Polar data table (+)
Polar graphs
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