GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 200,000 Max Cl/Cd: 63.48 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe614-il-200000.txt Download as CSV file: xf-goe614-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2201 0.06528 0.06151 -0.1236 0.9438 0.0581
-10.500 -0.2958 0.04878 0.04457 -0.1430 0.9280 0.0559
-10.250 -0.3223 0.04393 0.03939 -0.1450 0.9148 0.0553
-10.000 -0.3223 0.03876 0.03372 -0.1485 0.9088 0.0547
-9.750 -0.3232 0.03632 0.03098 -0.1468 0.8979 0.0547
-9.500 -0.3028 0.03329 0.02754 -0.1486 0.8932 0.0546
-9.250 -0.2731 0.03065 0.02454 -0.1510 0.8902 0.0546
-9.000 -0.2663 0.02928 0.02295 -0.1481 0.8787 0.0545
-8.750 -0.2332 0.02736 0.02077 -0.1500 0.8747 0.0545
-8.500 -0.2134 0.02614 0.01937 -0.1489 0.8662 0.0547
-8.250 -0.1846 0.02483 0.01790 -0.1494 0.8596 0.0549
-8.000 -0.1468 0.02348 0.01639 -0.1515 0.8553 0.0554
-7.750 -0.1312 0.02277 0.01559 -0.1493 0.8444 0.0557
-7.500 -0.0966 0.02172 0.01442 -0.1506 0.8384 0.0563
-7.250 -0.0772 0.02109 0.01371 -0.1490 0.8282 0.0568
-7.000 -0.0468 0.02025 0.01277 -0.1495 0.8208 0.0578
-6.750 -0.0276 0.01958 0.01212 -0.1480 0.8108 0.0589
-6.500 0.0001 0.01891 0.01140 -0.1480 0.8024 0.0603
-6.250 0.0202 0.01845 0.01090 -0.1465 0.7920 0.0615
-6.000 0.0479 0.01792 0.01026 -0.1464 0.7835 0.0630
-5.750 0.0676 0.01755 0.00983 -0.1447 0.7729 0.0646
-5.500 0.0951 0.01704 0.00925 -0.1447 0.7643 0.0674
-5.250 0.1144 0.01673 0.00891 -0.1429 0.7531 0.0709
-4.750 0.1621 0.01600 0.00819 -0.1411 0.7331 0.0950
-4.500 0.1884 0.01560 0.00777 -0.1408 0.7244 0.1228
-4.250 0.2091 0.01531 0.00760 -0.1394 0.7137 0.1515
-4.000 0.2357 0.01523 0.00753 -0.1391 0.7045 0.1811
-3.750 0.2599 0.01521 0.00745 -0.1381 0.6943 0.1987
-3.500 0.2854 0.01521 0.00737 -0.1375 0.6848 0.2141
-3.250 0.3101 0.01518 0.00728 -0.1368 0.6752 0.2282
-3.000 0.3351 0.01520 0.00721 -0.1361 0.6661 0.2423
-2.750 0.3601 0.01523 0.00714 -0.1354 0.6573 0.2569
-2.500 0.3853 0.01525 0.00714 -0.1348 0.6491 0.2723
-2.250 0.4087 0.01525 0.00712 -0.1339 0.6403 0.2856
-2.000 0.4358 0.01530 0.00707 -0.1336 0.6328 0.2997
-1.750 0.4580 0.01533 0.00709 -0.1324 0.6241 0.3123
-1.500 0.4866 0.01536 0.00705 -0.1325 0.6174 0.3261
-1.250 0.5078 0.01542 0.00713 -0.1312 0.6097 0.3404
-1.000 0.5331 0.01548 0.00714 -0.1306 0.6029 0.3563
-0.750 0.5607 0.01556 0.00718 -0.1305 0.5968 0.3720
-0.500 0.5816 0.01558 0.00727 -0.1292 0.5896 0.3871
-0.250 0.6076 0.01560 0.00728 -0.1288 0.5835 0.4040
0.000 0.6336 0.01568 0.00735 -0.1284 0.5778 0.4237
0.250 0.6550 0.01572 0.00748 -0.1271 0.5715 0.4455
0.500 0.6804 0.01576 0.00754 -0.1266 0.5662 0.4719
0.750 0.7090 0.01586 0.00764 -0.1268 0.5614 0.5021
1.000 0.7272 0.01590 0.00783 -0.1249 0.5555 0.5334
1.250 0.7498 0.01590 0.00794 -0.1238 0.5501 0.5697
1.500 0.7761 0.01592 0.00803 -0.1235 0.5456 0.6141
1.750 0.7967 0.01590 0.00824 -0.1220 0.5408 0.6705
2.000 0.8158 0.01572 0.00840 -0.1201 0.5348 0.7706
2.250 0.9215 0.01582 0.00853 -0.1361 0.5253 1.0000
2.500 0.9328 0.01596 0.00867 -0.1329 0.5185 1.0000
2.750 0.9526 0.01609 0.00868 -0.1313 0.5120 1.0000
3.000 0.9783 0.01632 0.00875 -0.1310 0.5065 1.0000
3.250 0.9921 0.01651 0.00895 -0.1283 0.5008 1.0000
3.500 1.0124 0.01670 0.00908 -0.1270 0.4958 1.0000
3.750 1.0376 0.01693 0.00919 -0.1265 0.4915 1.0000
4.000 1.0599 0.01721 0.00942 -0.1256 0.4871 1.0000
4.250 1.0755 0.01744 0.00967 -0.1234 0.4823 1.0000
4.500 1.0954 0.01765 0.00984 -0.1220 0.4776 1.0000
4.750 1.1205 0.01788 0.00996 -0.1216 0.4733 1.0000
5.000 1.1412 0.01817 0.01024 -0.1204 0.4690 1.0000
5.250 1.1552 0.01843 0.01053 -0.1179 0.4644 1.0000
5.500 1.1740 0.01866 0.01074 -0.1163 0.4600 1.0000
5.750 1.1976 0.01890 0.01090 -0.1157 0.4560 1.0000
6.000 1.2194 0.01921 0.01118 -0.1147 0.4518 1.0000
6.250 1.2276 0.01948 0.01152 -0.1112 0.4473 1.0000
6.500 1.2429 0.01974 0.01178 -0.1091 0.4429 1.0000
6.750 1.2640 0.01998 0.01197 -0.1080 0.4388 1.0000
7.000 1.2866 0.02031 0.01225 -0.1073 0.4345 1.0000
7.250 1.2918 0.02065 0.01268 -0.1034 0.4297 1.0000
7.500 1.3051 0.02092 0.01296 -0.1010 0.4247 1.0000
7.750 1.3265 0.02117 0.01314 -0.1001 0.4203 1.0000
8.000 1.3411 0.02157 0.01356 -0.0981 0.4159 1.0000
8.250 1.3484 0.02200 0.01407 -0.0950 0.4109 1.0000
8.500 1.3629 0.02234 0.01442 -0.0930 0.4063 1.0000
8.750 1.3871 0.02261 0.01459 -0.0927 0.4018 1.0000
9.000 1.3916 0.02319 0.01529 -0.0893 0.3970 1.0000
9.250 1.4000 0.02372 0.01587 -0.0866 0.3919 1.0000
9.500 1.4150 0.02411 0.01624 -0.0850 0.3871 1.0000
9.750 1.4317 0.02456 0.01667 -0.0837 0.3825 1.0000
10.000 1.4338 0.02534 0.01757 -0.0803 0.3771 1.0000
10.250 1.4439 0.02593 0.01819 -0.0782 0.3720 1.0000
10.500 1.4656 0.02627 0.01843 -0.0777 0.3677 1.0000
10.750 1.4651 0.02730 0.01962 -0.0744 0.3623 1.0000
11.000 1.4720 0.02815 0.02053 -0.0722 0.3573 1.0000
11.250 1.4866 0.02874 0.02110 -0.0710 0.3530 1.0000
11.500 1.4980 0.02954 0.02192 -0.0694 0.3485 1.0000
11.750 1.5002 0.03074 0.02325 -0.0670 0.3436 1.0000
12.000 1.5083 0.03170 0.02424 -0.0653 0.3389 1.0000
12.250 1.5269 0.03218 0.02464 -0.0646 0.3347 1.0000
12.500 1.5255 0.03375 0.02636 -0.0622 0.3300 1.0000
12.750 1.5294 0.03509 0.02781 -0.0604 0.3255 1.0000
13.000 1.5399 0.03608 0.02881 -0.0592 0.3217 1.0000
13.250 1.5573 0.03669 0.02937 -0.0586 0.3179 1.0000
13.500 1.5536 0.03869 0.03154 -0.0565 0.3137 1.0000
13.750 1.5550 0.04040 0.03334 -0.0550 0.3091 1.0000
14.000 1.5647 0.04151 0.03446 -0.0540 0.3050 1.0000
14.250 1.5704 0.04299 0.03597 -0.0529 0.3005 1.0000
14.500 1.5657 0.04539 0.03852 -0.0514 0.2959 1.0000
14.750 1.5677 0.04728 0.04046 -0.0503 0.2913 1.0000
15.000 1.5814 0.04812 0.04123 -0.0497 0.2865 1.0000
15.250 1.5687 0.05152 0.04483 -0.0484 0.2815 1.0000
15.500 1.5656 0.05408 0.04745 -0.0475 0.2762 1.0000
15.750 1.5788 0.05503 0.04834 -0.0470 0.2719 1.0000
16.000 1.5689 0.05846 0.05195 -0.0462 0.2675 1.0000
16.250 1.5617 0.06172 0.05533 -0.0457 0.2626 1.0000
16.500 1.5685 0.06341 0.05700 -0.0452 0.2579 1.0000
16.750 1.5644 0.06641 0.06010 -0.0449 0.2533 1.0000
17.000 1.5526 0.07042 0.06425 -0.0447 0.2483 1.0000
17.250 1.5558 0.07259 0.06642 -0.0444 0.2430 1.0000
17.500 1.5475 0.07627 0.07020 -0.0444 0.2375 1.0000
17.750 1.5341 0.08071 0.07477 -0.0446 0.2320 1.0000
18.000 1.5439 0.08207 0.07602 -0.0444 0.2259 1.0000
18.250 1.5192 0.08812 0.08231 -0.0450 0.2199 1.0000
18.500 1.5153 0.09140 0.08560 -0.0453 0.2135 1.0000
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Polar data table (+)
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