GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.5 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe366-il-1000000.txt Download as CSV file: xf-goe366-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.0649 0.09541 0.09318 -0.0931 0.8444 0.0166
-10.500 0.0722 0.09281 0.09056 -0.0936 0.8351 0.0167
-10.250 -0.0114 0.10235 0.10014 -0.0892 0.8699 0.0166
-10.000 -0.0024 0.09988 0.09760 -0.0897 0.8606 0.0167
-9.750 0.0069 0.09743 0.09514 -0.0906 0.8507 0.0167
-9.500 0.0159 0.09506 0.09272 -0.0916 0.8408 0.0168
-9.250 0.0250 0.09270 0.09032 -0.0926 0.8294 0.0170
-9.000 0.0342 0.09034 0.08791 -0.0937 0.8176 0.0171
-8.750 0.0433 0.08798 0.08551 -0.0948 0.8061 0.0174
-8.500 0.0525 0.08558 0.08305 -0.0961 0.7946 0.0176
-8.250 0.0618 0.08312 0.08055 -0.0975 0.7845 0.0179
-8.000 0.0710 0.08066 0.07803 -0.0989 0.7753 0.0183
-7.750 0.0807 0.07806 0.07542 -0.1006 0.7679 0.0187
-7.500 0.0900 0.07532 0.07264 -0.1032 0.7606 0.0190
-7.250 0.0979 0.07266 0.06996 -0.1061 0.7545 0.0191
-7.000 0.1117 0.06955 0.06683 -0.1113 0.7486 0.0191
-6.750 0.1291 0.06615 0.06338 -0.1171 0.7430 0.0192
-6.500 0.1492 0.06256 0.05975 -0.1229 0.7384 0.0192
-6.000 0.1852 0.05599 0.05311 -0.1294 0.7289 0.0193
-5.750 0.2020 0.05373 0.05080 -0.1306 0.7240 0.0194
-5.500 0.2218 0.05136 0.04843 -0.1326 0.7201 0.0195
-5.250 0.2433 0.04897 0.04601 -0.1351 0.7154 0.0196
-5.000 0.2661 0.04660 0.04357 -0.1378 0.7106 0.0199
-4.750 0.2903 0.04419 0.04108 -0.1405 0.7058 0.0201
-4.500 0.3162 0.04168 0.03852 -0.1432 0.7017 0.0205
-4.250 0.3429 0.03916 0.03593 -0.1458 0.6966 0.0211
-4.000 0.3764 0.03613 0.03272 -0.1491 0.6914 0.0220
-3.750 0.4083 0.03321 0.02961 -0.1513 0.6867 0.0221
-3.500 0.4376 0.03060 0.02685 -0.1527 0.6816 0.0221
-3.250 0.4622 0.02785 0.02396 -0.1537 0.6756 0.0222
-3.000 0.4855 0.02628 0.02231 -0.1542 0.6692 0.0224
-2.750 0.5108 0.02491 0.02088 -0.1548 0.6616 0.0225
-2.500 0.5359 0.02367 0.01952 -0.1551 0.6533 0.0228
-2.250 0.5627 0.02235 0.01811 -0.1555 0.6438 0.0231
-2.000 0.5893 0.02106 0.01667 -0.1556 0.6322 0.0237
-1.750 0.6215 0.01936 0.01448 -0.1548 0.6175 0.0253
-1.500 0.6457 0.01756 0.01249 -0.1548 0.5966 0.0256
-1.250 0.6689 0.01683 0.01160 -0.1544 0.5718 0.0258
-1.000 0.6929 0.01627 0.01087 -0.1540 0.5513 0.0260
-0.750 0.7177 0.01573 0.01017 -0.1536 0.5349 0.0264
-0.250 0.7714 0.01511 0.00903 -0.1524 0.5103 0.0288
0.000 0.7969 0.01389 0.00767 -0.1522 0.5005 0.0292
0.250 0.8230 0.01335 0.00709 -0.1521 0.4917 0.0297
0.500 0.8488 0.01302 0.00668 -0.1518 0.4837 0.0303
0.750 0.8763 0.01318 0.00663 -0.1514 0.4765 0.0327
1.000 0.9018 0.01233 0.00573 -0.1512 0.4689 0.0338
1.250 0.9285 0.01207 0.00546 -0.1511 0.4624 0.0353
1.500 0.9547 0.01184 0.00513 -0.1508 0.4554 0.0386
1.750 0.9804 0.01185 0.00508 -0.1504 0.4488 0.0416
2.000 1.0070 0.01152 0.00477 -0.1503 0.4433 0.0456
2.250 1.0325 0.01142 0.00465 -0.1500 0.4371 0.0517
3.000 1.1111 0.01106 0.00410 -0.1487 0.4201 0.0332
3.250 1.1363 0.01111 0.00412 -0.1482 0.4145 0.0328
3.500 1.1627 0.01103 0.00406 -0.1481 0.4098 0.0330
3.750 1.1881 0.01103 0.00404 -0.1477 0.4046 0.0336
4.000 1.2121 0.01114 0.00413 -0.1471 0.3989 0.0342
4.250 1.2382 0.01118 0.00419 -0.1469 0.3946 0.0357
4.500 1.2628 0.01128 0.00429 -0.1464 0.3889 0.0368
4.750 1.2856 0.01147 0.00442 -0.1456 0.3827 0.0377
5.000 1.3108 0.01155 0.00452 -0.1453 0.3787 0.0404
5.250 1.3347 0.01167 0.00465 -0.1447 0.3743 0.0466
5.500 1.3557 0.01055 0.00517 -0.1440 0.3699 1.0000
5.750 1.3769 0.01079 0.00537 -0.1428 0.3649 1.0000
6.000 1.4005 0.01096 0.00552 -0.1422 0.3605 1.0000
6.250 1.4224 0.01118 0.00572 -0.1413 0.3557 1.0000
6.500 1.4429 0.01147 0.00597 -0.1401 0.3508 1.0000
6.750 1.4654 0.01169 0.00620 -0.1394 0.3473 1.0000
7.000 1.4881 0.01190 0.00641 -0.1387 0.3437 1.0000
7.250 1.5096 0.01216 0.00667 -0.1378 0.3398 1.0000
7.500 1.5295 0.01248 0.00697 -0.1366 0.3358 1.0000
7.750 1.5502 0.01278 0.00728 -0.1356 0.3321 1.0000
8.000 1.5726 0.01301 0.00753 -0.1350 0.3285 1.0000
8.250 1.5930 0.01333 0.00784 -0.1340 0.3239 1.0000
8.500 1.6109 0.01376 0.00825 -0.1326 0.3184 1.0000
8.750 1.6323 0.01404 0.00855 -0.1319 0.3140 1.0000
9.000 1.6523 0.01439 0.00890 -0.1309 0.3092 1.0000
9.250 1.6704 0.01484 0.00934 -0.1297 0.3044 1.0000
9.500 1.6890 0.01526 0.00978 -0.1286 0.3002 1.0000
9.750 1.7093 0.01562 0.01017 -0.1278 0.2959 1.0000
10.000 1.7266 0.01612 0.01066 -0.1265 0.2902 1.0000
10.250 1.7434 0.01667 0.01120 -0.1253 0.2844 1.0000
10.500 1.7617 0.01714 0.01170 -0.1243 0.2782 1.0000
11.000 1.7938 0.01837 0.01292 -0.1217 0.2650 1.0000
11.250 1.8074 0.01913 0.01367 -0.1202 0.2578 1.0000
11.500 1.8228 0.01981 0.01436 -0.1189 0.2504 1.0000
11.750 1.8335 0.02079 0.01530 -0.1171 0.2406 1.0000
12.000 1.8458 0.02169 0.01618 -0.1156 0.2303 1.0000
12.250 1.8551 0.02279 0.01726 -0.1138 0.2190 1.0000
12.500 1.8598 0.02423 0.01863 -0.1115 0.2034 1.0000
12.750 1.8585 0.02614 0.02043 -0.1087 0.1839 1.0000
13.000 1.8529 0.02843 0.02261 -0.1057 0.1615 1.0000
13.250 1.8456 0.03100 0.02507 -0.1028 0.1422 1.0000
13.500 1.8421 0.03339 0.02741 -0.1004 0.1293 1.0000
13.750 1.8401 0.03574 0.02974 -0.0984 0.1200 1.0000
14.000 1.8423 0.03782 0.03184 -0.0969 0.1138 1.0000
14.250 1.8416 0.04022 0.03425 -0.0953 0.1075 1.0000
14.500 1.8443 0.04234 0.03641 -0.0940 0.1025 1.0000
14.750 1.8414 0.04505 0.03912 -0.0925 0.0965 1.0000
15.000 1.8431 0.04738 0.04150 -0.0914 0.0911 1.0000
15.250 1.8368 0.05058 0.04469 -0.0901 0.0836 1.0000
15.500 1.8270 0.05422 0.04832 -0.0887 0.0740 1.0000
15.750 1.8132 0.05844 0.05252 -0.0875 0.0639 1.0000
16.000 1.7951 0.06335 0.05743 -0.0864 0.0543 1.0000
16.250 1.7756 0.06858 0.06268 -0.0856 0.0455 1.0000
16.500 1.7509 0.07466 0.06878 -0.0851 0.0361 1.0000
16.750 1.7222 0.08148 0.07562 -0.0849 0.0254 1.0000
17.000 1.7014 0.08737 0.08157 -0.0850 0.0209 1.0000
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