GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 200,000 Max Cl/Cd: 85.96 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe195-il-200000.txt Download as CSV file: xf-goe195-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 195 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3351 0.09846 0.09491 -0.0327 1.0000 0.0509
-8.000 -0.3554 0.09784 0.09440 -0.0315 1.0000 0.0514
-7.750 -0.3694 0.09637 0.09302 -0.0317 1.0000 0.0516
-7.500 -0.3730 0.09220 0.08891 -0.0298 1.0000 0.0523
-7.250 -0.3669 0.08977 0.08650 -0.0258 1.0000 0.0532
-7.000 -0.3654 0.08796 0.08472 -0.0233 1.0000 0.0542
-6.750 -0.3673 0.08623 0.08303 -0.0215 1.0000 0.0552
-6.500 -0.3708 0.08444 0.08130 -0.0204 1.0000 0.0565
-6.250 -0.3638 0.08167 0.07855 -0.0229 0.9986 0.0589
-6.000 -0.3166 0.07252 0.06933 -0.0452 0.9915 0.0642
-5.750 -0.2958 0.07076 0.06757 -0.0434 0.9879 0.0665
-5.500 -0.2309 0.06117 0.05779 -0.0690 0.9817 0.0766
-5.250 -0.2123 0.05951 0.05616 -0.0665 0.9766 0.0782
-5.000 -0.1487 0.05132 0.04769 -0.0864 0.9722 0.0904
-4.750 -0.1269 0.05004 0.04648 -0.0848 0.9672 0.0922
-4.500 -0.0782 0.04474 0.04097 -0.0959 0.9618 0.1054
-4.250 -0.0475 0.04347 0.03974 -0.0965 0.9586 0.1091
-4.000 -0.0004 0.03913 0.03519 -0.1050 0.9549 0.1220
-3.750 0.0796 0.02172 0.01535 -0.1231 0.9538 0.0647
-3.500 0.1174 0.02066 0.01397 -0.1248 0.9480 0.0635
-3.250 0.1594 0.01886 0.01194 -0.1277 0.9450 0.0621
-3.000 0.2031 0.01733 0.01018 -0.1307 0.9428 0.0614
-2.750 0.2363 0.01636 0.00908 -0.1315 0.9352 0.0614
-2.500 0.2743 0.01543 0.00809 -0.1332 0.9304 0.0618
-2.250 0.3137 0.01461 0.00722 -0.1351 0.9268 0.0636
-2.000 0.3431 0.01384 0.00650 -0.1351 0.9166 0.0656
-1.750 0.3784 0.01320 0.00588 -0.1362 0.9103 0.0676
-1.500 0.4084 0.01278 0.00542 -0.1361 0.8999 0.0706
-1.250 0.4387 0.01242 0.00501 -0.1361 0.8895 0.0750
-1.000 0.4703 0.01192 0.00454 -0.1362 0.8799 0.0890
-0.750 0.4992 0.01131 0.00448 -0.1362 0.8673 0.2529
-0.500 0.5270 0.01128 0.00445 -0.1356 0.8532 0.3018
-0.250 0.5547 0.01117 0.00432 -0.1351 0.8383 0.3286
0.000 0.5823 0.01103 0.00416 -0.1346 0.8222 0.3484
0.250 0.6097 0.01091 0.00404 -0.1340 0.8054 0.3744
0.500 0.6364 0.01082 0.00399 -0.1334 0.7862 0.3994
0.750 0.6630 0.01076 0.00398 -0.1328 0.7670 0.4325
1.000 0.6895 0.01072 0.00403 -0.1322 0.7483 0.4824
1.250 0.7150 0.01056 0.00409 -0.1314 0.7303 0.5820
1.500 0.7388 0.00989 0.00397 -0.1298 0.7123 1.0000
1.750 0.7654 0.01008 0.00399 -0.1293 0.6935 1.0000
2.000 0.7921 0.01027 0.00405 -0.1288 0.6771 1.0000
2.250 0.8191 0.01047 0.00413 -0.1284 0.6634 1.0000
2.500 0.8461 0.01066 0.00423 -0.1280 0.6506 1.0000
2.750 0.8730 0.01084 0.00437 -0.1277 0.6381 1.0000
3.000 0.8997 0.01103 0.00449 -0.1273 0.6252 1.0000
3.250 0.9260 0.01122 0.00462 -0.1268 0.6115 1.0000
3.500 0.9523 0.01142 0.00475 -0.1263 0.5983 1.0000
3.750 0.9786 0.01166 0.00492 -0.1258 0.5860 1.0000
4.250 1.0307 0.01219 0.00535 -0.1248 0.5603 1.0000
4.500 1.0562 0.01248 0.00560 -0.1241 0.5459 1.0000
4.750 1.0810 0.01280 0.00584 -0.1234 0.5291 1.0000
5.000 1.1057 0.01311 0.00612 -0.1227 0.5123 1.0000
5.250 1.1306 0.01338 0.00640 -0.1220 0.4971 1.0000
5.500 1.1554 0.01362 0.00669 -0.1213 0.4820 1.0000
5.750 1.1794 0.01386 0.00695 -0.1204 0.4641 1.0000
6.000 1.2033 0.01404 0.00720 -0.1195 0.4426 1.0000
6.250 1.2266 0.01427 0.00744 -0.1186 0.4185 1.0000
6.500 1.2492 0.01456 0.00771 -0.1175 0.3887 1.0000
6.750 1.2700 0.01502 0.00806 -0.1162 0.3502 1.0000
7.000 1.2877 0.01578 0.00857 -0.1145 0.3029 1.0000
7.250 1.3055 0.01662 0.00921 -0.1130 0.2618 1.0000
7.500 1.3224 0.01757 0.00995 -0.1113 0.2207 1.0000
7.750 1.3381 0.01864 0.01079 -0.1095 0.1706 1.0000
8.000 1.3493 0.02016 0.01190 -0.1072 0.1166 1.0000
8.250 1.3597 0.02173 0.01323 -0.1046 0.0805 1.0000
8.500 1.3730 0.02295 0.01435 -0.1024 0.0639 1.0000
8.750 1.3861 0.02408 0.01548 -0.1001 0.0567 1.0000
9.000 1.3972 0.02529 0.01671 -0.0976 0.0521 1.0000
9.250 1.4043 0.02661 0.01809 -0.0945 0.0491 1.0000
9.500 1.4127 0.02781 0.01938 -0.0917 0.0464 1.0000
9.750 1.4188 0.02922 0.02085 -0.0887 0.0442 1.0000
10.000 1.4209 0.03106 0.02270 -0.0854 0.0425 1.0000
10.250 1.4249 0.03300 0.02471 -0.0825 0.0411 1.0000
10.500 1.4340 0.03453 0.02637 -0.0802 0.0399 1.0000
10.750 1.4427 0.03615 0.02811 -0.0780 0.0383 1.0000
11.000 1.4512 0.03787 0.02989 -0.0760 0.0367 1.0000
11.250 1.4608 0.03974 0.03180 -0.0741 0.0355 1.0000
11.500 1.4776 0.04216 0.03421 -0.0727 0.0342 1.0000
11.750 1.4956 0.04487 0.03709 -0.0715 0.0332 1.0000
12.000 1.5018 0.04678 0.03925 -0.0693 0.0326 1.0000
12.250 1.5065 0.04890 0.04160 -0.0673 0.0318 1.0000
12.500 1.5102 0.05124 0.04415 -0.0653 0.0309 1.0000
12.750 1.5130 0.05381 0.04694 -0.0635 0.0302 1.0000
13.000 1.5142 0.05669 0.05004 -0.0617 0.0298 1.0000
13.250 1.5128 0.05981 0.05338 -0.0601 0.0294 1.0000
13.500 1.5084 0.06321 0.05702 -0.0586 0.0292 1.0000
13.750 1.5010 0.06696 0.06100 -0.0573 0.0290 1.0000
14.000 1.4900 0.07110 0.06542 -0.0565 0.0289 1.0000
14.250 1.4746 0.07586 0.07045 -0.0561 0.0289 1.0000
14.500 1.4556 0.08121 0.07609 -0.0565 0.0290 1.0000
14.750 1.4333 0.08727 0.08244 -0.0577 0.0292 1.0000
15.000 1.4078 0.09419 0.08963 -0.0600 0.0295 1.0000
15.250 1.3806 0.10197 0.09770 -0.0635 0.0298 1.0000
15.500 1.3523 0.11073 0.10672 -0.0681 0.0302 1.0000
15.750 1.3234 0.12036 0.11658 -0.0739 0.0307 1.0000
16.000 1.2933 0.13120 0.12764 -0.0810 0.0312 1.0000
16.250 1.2613 0.14380 0.14042 -0.0898 0.0318 1.0000
16.500 1.2281 0.15834 0.15509 -0.0999 0.0327 1.0000
16.750 1.2168 0.16641 0.16318 -0.1035 0.0336 1.0000
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Polar data table (+)
Polar graphs
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