GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 395 AIRFOIL (goe395-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.32 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe395-il-1000000.txt Download as CSV file: xf-goe395-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 395 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1571 0.08436 0.08193 -0.0425 0.7522 0.0167
-8.250 -0.1540 0.08068 0.07825 -0.0445 0.7508 0.0169
-8.000 -0.1487 0.07713 0.07470 -0.0460 0.7495 0.0170
-7.750 -0.1432 0.07351 0.07107 -0.0474 0.7481 0.0170
-7.500 -0.1403 0.06896 0.06652 -0.0484 0.7467 0.0173
-7.250 -0.1293 0.06670 0.06425 -0.0489 0.7453 0.0176
-7.000 -0.1188 0.06434 0.06189 -0.0499 0.7439 0.0180
-6.750 -0.1088 0.06186 0.05942 -0.0511 0.7430 0.0186
-6.500 -0.0960 0.05877 0.05634 -0.0537 0.7419 0.0197
-6.250 -0.0783 0.05370 0.05126 -0.0614 0.7407 0.0214
-6.000 -0.0602 0.04921 0.04675 -0.0665 0.7395 0.0215
-5.750 -0.0445 0.04269 0.04022 -0.0727 0.7385 0.0220
-5.500 -0.0258 0.04099 0.03851 -0.0736 0.7372 0.0225
-5.250 -0.0045 0.03875 0.03625 -0.0760 0.7355 0.0231
-5.000 0.0195 0.03603 0.03350 -0.0797 0.7335 0.0245
-4.500 0.1653 0.01331 0.00875 -0.1436 0.7357 0.0282
-4.250 0.1944 0.01248 0.00779 -0.1442 0.7337 0.0290
-4.000 0.2231 0.01204 0.00724 -0.1444 0.7316 0.0298
-3.750 0.2522 0.01135 0.00636 -0.1448 0.7295 0.0303
-3.500 0.2814 0.01071 0.00558 -0.1451 0.7280 0.0308
-3.250 0.3106 0.01016 0.00491 -0.1454 0.7265 0.0314
-3.000 0.3396 0.00970 0.00435 -0.1455 0.7249 0.0320
-2.750 0.3685 0.00937 0.00394 -0.1457 0.7230 0.0328
-2.500 0.3973 0.00911 0.00362 -0.1457 0.7209 0.0336
-2.250 0.4260 0.00887 0.00331 -0.1458 0.7187 0.0340
-2.000 0.4548 0.00856 0.00292 -0.1458 0.7164 0.0345
-1.750 0.4837 0.00824 0.00249 -0.1459 0.7141 0.0356
-1.500 0.5125 0.00800 0.00224 -0.1460 0.7124 0.0370
-1.250 0.5413 0.00783 0.00207 -0.1460 0.7105 0.0385
-1.000 0.5701 0.00770 0.00193 -0.1461 0.7086 0.0405
-0.750 0.5987 0.00760 0.00182 -0.1461 0.7064 0.0427
-0.500 0.6274 0.00745 0.00171 -0.1461 0.7040 0.0521
-0.250 0.6558 0.00742 0.00175 -0.1461 0.7016 0.0685
0.000 0.6840 0.00751 0.00183 -0.1460 0.6989 0.0752
0.250 0.7125 0.00747 0.00182 -0.1460 0.6969 0.0790
0.500 0.7410 0.00740 0.00180 -0.1460 0.6937 0.0835
0.750 0.7693 0.00736 0.00177 -0.1459 0.6898 0.0868
1.000 0.7975 0.00735 0.00176 -0.1459 0.6864 0.0895
1.250 0.8257 0.00735 0.00174 -0.1458 0.6830 0.0928
1.500 0.8542 0.00725 0.00172 -0.1459 0.6797 0.0976
1.750 0.8826 0.00719 0.00168 -0.1458 0.6745 0.1009
2.000 0.9105 0.00719 0.00166 -0.1457 0.6686 0.1041
2.250 0.9390 0.00709 0.00163 -0.1458 0.6626 0.1086
2.500 0.9672 0.00704 0.00162 -0.1457 0.6563 0.1139
2.750 0.9954 0.00701 0.00162 -0.1457 0.6486 0.1189
3.000 1.0234 0.00697 0.00161 -0.1457 0.6362 0.1306
3.250 1.0510 0.00695 0.00162 -0.1455 0.6104 0.1593
3.500 1.0752 0.00730 0.00184 -0.1451 0.5332 0.2775
3.750 1.1002 0.00752 0.00230 -0.1449 0.4913 0.5529
4.000 1.1263 0.00776 0.00251 -0.1446 0.4668 0.5959
4.250 1.1484 0.00730 0.00270 -0.1435 0.4469 1.0000
4.500 1.1746 0.00757 0.00288 -0.1433 0.4253 1.0000
4.750 1.2006 0.00787 0.00308 -0.1430 0.4046 1.0000
5.000 1.2256 0.00828 0.00333 -0.1426 0.3736 1.0000
5.250 1.2505 0.00868 0.00359 -0.1422 0.3442 1.0000
5.500 1.2755 0.00905 0.00385 -0.1418 0.3180 1.0000
5.750 1.2996 0.00951 0.00416 -0.1413 0.2869 1.0000
6.000 1.3219 0.01017 0.00457 -0.1405 0.2408 1.0000
6.250 1.3410 0.01117 0.00519 -0.1394 0.1733 1.0000
6.500 1.3617 0.01196 0.00575 -0.1384 0.1343 1.0000
6.750 1.3843 0.01251 0.00619 -0.1377 0.1156 1.0000
7.000 1.4076 0.01295 0.00657 -0.1370 0.1027 1.0000
7.250 1.4303 0.01344 0.00698 -0.1363 0.0868 1.0000
7.500 1.4507 0.01414 0.00751 -0.1353 0.0614 1.0000
7.750 1.4708 0.01485 0.00811 -0.1342 0.0439 1.0000
8.000 1.4871 0.01590 0.00895 -0.1325 0.0191 1.0000
8.250 1.5070 0.01655 0.00960 -0.1314 0.0161 1.0000
8.500 1.5265 0.01720 0.01030 -0.1301 0.0142 1.0000
8.750 1.5465 0.01776 0.01091 -0.1289 0.0135 1.0000
9.000 1.5652 0.01839 0.01159 -0.1276 0.0126 1.0000
9.250 1.5820 0.01914 0.01238 -0.1260 0.0118 1.0000
9.500 1.5935 0.02024 0.01357 -0.1236 0.0109 1.0000
9.750 1.6067 0.02096 0.01436 -0.1214 0.0105 1.0000
10.000 1.6203 0.02167 0.01512 -0.1193 0.0102 1.0000
10.250 1.6322 0.02251 0.01603 -0.1172 0.0098 1.0000
10.500 1.6432 0.02347 0.01705 -0.1150 0.0094 1.0000
10.750 1.6537 0.02451 0.01815 -0.1130 0.0090 1.0000
11.000 1.6629 0.02568 0.01939 -0.1109 0.0087 1.0000
11.250 1.6702 0.02707 0.02084 -0.1088 0.0084 1.0000
11.500 1.6727 0.02894 0.02281 -0.1064 0.0081 1.0000
11.750 1.6662 0.03171 0.02572 -0.1034 0.0078 1.0000
12.000 1.6717 0.03346 0.02757 -0.1016 0.0077 1.0000
12.250 1.6795 0.03503 0.02922 -0.1001 0.0076 1.0000
12.500 1.6860 0.03675 0.03102 -0.0986 0.0074 1.0000
12.750 1.6903 0.03872 0.03309 -0.0970 0.0073 1.0000
13.000 1.6943 0.04072 0.03518 -0.0956 0.0071 1.0000
13.250 1.6978 0.04282 0.03737 -0.0941 0.0070 1.0000
13.500 1.7010 0.04498 0.03962 -0.0928 0.0068 1.0000
13.750 1.7036 0.04720 0.04193 -0.0916 0.0066 1.0000
14.000 1.7049 0.04961 0.04442 -0.0904 0.0064 1.0000
14.250 1.7054 0.05215 0.04705 -0.0892 0.0063 1.0000
14.500 1.7049 0.05487 0.04985 -0.0882 0.0062 1.0000
14.750 1.7029 0.05786 0.05294 -0.0873 0.0061 1.0000
15.000 1.6996 0.06113 0.05630 -0.0866 0.0060 1.0000
15.250 1.6942 0.06475 0.06002 -0.0860 0.0059 1.0000
15.500 1.6865 0.06879 0.06417 -0.0856 0.0058 1.0000
15.750 1.6756 0.07343 0.06893 -0.0854 0.0057 1.0000
16.000 1.6623 0.07854 0.07418 -0.0854 0.0056 1.0000
16.250 1.6425 0.08464 0.08045 -0.0856 0.0055 1.0000
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Polar data table (+)
Polar graphs
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