GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 200,000 Max Cl/Cd: 83.43 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe240-il-200000.txt Download as CSV file: xf-goe240-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3239 0.08837 0.08524 -0.0225 1.0000 0.0324
-6.750 -0.3295 0.08665 0.08359 -0.0212 1.0000 0.0329
-6.500 -0.3446 0.08587 0.08291 -0.0181 1.0000 0.0331
-6.250 -0.3187 0.08163 0.07865 -0.0252 0.9956 0.0347
-6.000 -0.2571 0.07624 0.07309 -0.0468 0.9870 0.0379
-5.750 -0.2251 0.06965 0.06644 -0.0547 0.9833 0.0388
-5.500 -0.2096 0.06633 0.06315 -0.0536 0.9775 0.0404
-5.250 -0.1747 0.06246 0.05922 -0.0596 0.9729 0.0436
-5.000 -0.1065 0.05653 0.05292 -0.0776 0.9658 0.0487
-4.750 -0.0891 0.05271 0.04918 -0.0778 0.9612 0.0502
-4.500 -0.0548 0.04957 0.04598 -0.0818 0.9581 0.0537
-4.250 -0.0036 0.04493 0.04100 -0.0912 0.9523 0.0610
-4.000 0.0225 0.04227 0.03837 -0.0928 0.9469 0.0635
-3.750 0.0783 0.03927 0.03478 -0.1004 0.9431 0.0729
-3.500 0.0989 0.03591 0.03154 -0.1010 0.9355 0.0747
-3.250 0.1436 0.03575 0.03080 -0.1041 0.9300 0.0857
-3.000 0.1669 0.03104 0.02626 -0.1057 0.9239 0.0880
-2.750 0.1947 0.02905 0.02423 -0.1065 0.9167 0.0917
-2.500 0.2301 0.02702 0.02178 -0.1082 0.9106 0.1014
-2.250 0.2567 0.02518 0.01992 -0.1085 0.9027 0.1052
-2.000 0.2872 0.02359 0.01810 -0.1091 0.8954 0.1172
-1.750 0.3165 0.02225 0.01656 -0.1094 0.8868 0.1309
-1.500 0.3546 0.01856 0.01192 -0.1085 0.8780 0.0743
-1.250 0.3842 0.01696 0.01008 -0.1080 0.8687 0.0676
-1.000 0.4128 0.01562 0.00843 -0.1074 0.8579 0.0646
-0.750 0.4403 0.01490 0.00754 -0.1067 0.8467 0.0658
-0.500 0.4681 0.01426 0.00675 -0.1062 0.8369 0.0666
-0.250 0.4958 0.01364 0.00598 -0.1056 0.8274 0.0665
0.000 0.5224 0.01318 0.00547 -0.1050 0.8161 0.0674
0.250 0.5491 0.01283 0.00509 -0.1043 0.8053 0.0693
0.500 0.5759 0.01261 0.00480 -0.1037 0.7948 0.0722
0.750 0.6024 0.01230 0.00453 -0.1032 0.7835 0.0786
1.000 0.6287 0.01211 0.00437 -0.1026 0.7711 0.0946
1.250 0.6528 0.01101 0.00429 -0.1021 0.7585 0.4586
1.500 0.6808 0.01001 0.00415 -0.1014 0.7445 1.0000
1.750 0.7066 0.01007 0.00406 -0.1006 0.7287 1.0000
2.000 0.7324 0.01012 0.00398 -0.0998 0.7119 1.0000
2.250 0.7583 0.01017 0.00393 -0.0991 0.6952 1.0000
2.500 0.7843 0.01024 0.00389 -0.0984 0.6783 1.0000
2.750 0.8100 0.01030 0.00389 -0.0978 0.6581 1.0000
3.000 0.8356 0.01039 0.00387 -0.0971 0.6366 1.0000
3.250 0.8609 0.01050 0.00389 -0.0964 0.6128 1.0000
3.500 0.8859 0.01068 0.00392 -0.0956 0.5884 1.0000
3.750 0.9106 0.01092 0.00401 -0.0949 0.5637 1.0000
4.000 0.9353 0.01121 0.00417 -0.0942 0.5407 1.0000
4.250 0.9601 0.01153 0.00440 -0.0935 0.5199 1.0000
4.500 0.9848 0.01187 0.00464 -0.0929 0.4999 1.0000
4.750 1.0093 0.01217 0.00490 -0.0923 0.4774 1.0000
5.000 1.0335 0.01249 0.00515 -0.0916 0.4537 1.0000
5.250 1.0574 0.01281 0.00544 -0.0909 0.4289 1.0000
5.500 1.0812 0.01316 0.00572 -0.0902 0.4037 1.0000
5.750 1.1043 0.01357 0.00605 -0.0894 0.3788 1.0000
6.000 1.1268 0.01404 0.00643 -0.0885 0.3548 1.0000
6.250 1.1489 0.01456 0.00688 -0.0876 0.3295 1.0000
6.500 1.1704 0.01512 0.00734 -0.0867 0.3025 1.0000
6.750 1.1917 0.01569 0.00782 -0.0858 0.2757 1.0000
7.000 1.2129 0.01627 0.00830 -0.0848 0.2507 1.0000
7.250 1.2343 0.01682 0.00882 -0.0839 0.2269 1.0000
7.500 1.2550 0.01743 0.00935 -0.0830 0.2073 1.0000
7.750 1.2758 0.01802 0.00992 -0.0820 0.1898 1.0000
8.000 1.2963 0.01863 0.01053 -0.0810 0.1766 1.0000
8.250 1.3164 0.01927 0.01119 -0.0800 0.1619 1.0000
8.500 1.3352 0.02000 0.01188 -0.0788 0.1416 1.0000
8.750 1.3527 0.02086 0.01263 -0.0774 0.1095 1.0000
9.000 1.3573 0.02296 0.01425 -0.0744 0.0529 1.0000
9.250 1.3667 0.02455 0.01595 -0.0718 0.0401 1.0000
9.500 1.3778 0.02585 0.01732 -0.0694 0.0338 1.0000
9.750 1.3873 0.02703 0.01864 -0.0668 0.0307 1.0000
10.000 1.3968 0.02815 0.01986 -0.0644 0.0280 1.0000
10.250 1.4010 0.02968 0.02145 -0.0615 0.0262 1.0000
10.500 1.4007 0.03157 0.02346 -0.0584 0.0253 1.0000
10.750 1.4030 0.03338 0.02541 -0.0558 0.0247 1.0000
11.000 1.4043 0.03540 0.02756 -0.0534 0.0241 1.0000
11.250 1.4054 0.03757 0.02986 -0.0513 0.0236 1.0000
11.500 1.4067 0.03988 0.03229 -0.0494 0.0231 1.0000
11.750 1.4086 0.04227 0.03481 -0.0477 0.0227 1.0000
12.000 1.4114 0.04469 0.03734 -0.0460 0.0224 1.0000
12.250 1.4152 0.04708 0.03984 -0.0445 0.0219 1.0000
12.500 1.4188 0.04952 0.04238 -0.0432 0.0214 1.0000
12.750 1.4213 0.05210 0.04505 -0.0420 0.0207 1.0000
13.000 1.4239 0.05493 0.04797 -0.0407 0.0201 1.0000
13.250 1.4276 0.05801 0.05120 -0.0391 0.0198 1.0000
13.500 1.4303 0.06128 0.05467 -0.0378 0.0197 1.0000
13.750 1.4296 0.06487 0.05849 -0.0368 0.0197 1.0000
14.000 1.4258 0.06865 0.06251 -0.0361 0.0197 1.0000
14.250 1.4192 0.07267 0.06676 -0.0359 0.0197 1.0000
14.500 1.4104 0.07697 0.07129 -0.0360 0.0198 1.0000
14.750 1.3994 0.08158 0.07613 -0.0367 0.0199 1.0000
15.000 1.3860 0.08669 0.08149 -0.0380 0.0201 1.0000
15.250 1.3700 0.09249 0.08755 -0.0400 0.0203 1.0000
15.500 1.3506 0.09925 0.09460 -0.0429 0.0205 1.0000
15.750 1.3290 0.10699 0.10262 -0.0467 0.0209 1.0000
16.000 1.3035 0.11603 0.11194 -0.0520 0.0213 1.0000
16.250 1.2758 0.12630 0.12246 -0.0587 0.0216 1.0000
16.500 1.2482 0.13750 0.13389 -0.0663 0.0220 1.0000
16.750 1.2197 0.15002 0.14660 -0.0750 0.0224 1.0000
17.000 1.1859 0.16563 0.16237 -0.0858 0.0230 1.0000
17.250 1.1502 0.18402 0.18082 -0.0975 0.0242 1.0000
17.500 1.1399 0.19349 0.19025 -0.1026 0.0251 1.0000
17.750 0.8929 0.16397 0.16094 -0.0647 0.0255 1.0000
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Polar data table (+)
Polar graphs
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