GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 418 AIRFOIL (goe418-il) Reynolds number: 500,000 Max Cl/Cd: 90.25 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe418-il-500000-n5.txt Download as CSV file: xf-goe418-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 418 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9525 0.03359 0.02978 -0.0961 0.9992 0.0400
-13.250 -0.9298 0.03057 0.02661 -0.0998 0.9942 0.0405
-13.000 -0.9061 0.02857 0.02448 -0.1019 0.9881 0.0409
-12.750 -0.8798 0.02688 0.02266 -0.1039 0.9824 0.0413
-12.500 -0.8555 0.02548 0.02114 -0.1048 0.9755 0.0418
-12.250 -0.8284 0.02419 0.01971 -0.1061 0.9700 0.0423
-12.000 -0.8007 0.02300 0.01838 -0.1072 0.9641 0.0429
-11.750 -0.7713 0.02188 0.01711 -0.1085 0.9581 0.0435
-11.500 -0.7397 0.02084 0.01589 -0.1101 0.9532 0.0441
-11.250 -0.7105 0.01995 0.01489 -0.1110 0.9453 0.0447
-11.000 -0.6774 0.01921 0.01410 -0.1125 0.9385 0.0453
-10.750 -0.6470 0.01856 0.01338 -0.1133 0.9294 0.0458
-10.250 -0.5886 0.01739 0.01201 -0.1143 0.9107 0.0471
-10.000 -0.5610 0.01685 0.01134 -0.1143 0.9012 0.0478
-9.750 -0.5356 0.01636 0.01072 -0.1138 0.8904 0.0484
-9.500 -0.5097 0.01590 0.01013 -0.1134 0.8800 0.0491
-9.250 -0.4849 0.01546 0.00962 -0.1128 0.8688 0.0498
-9.000 -0.4596 0.01509 0.00919 -0.1122 0.8587 0.0505
-8.750 -0.4341 0.01475 0.00878 -0.1116 0.8475 0.0513
-8.500 -0.4086 0.01442 0.00836 -0.1109 0.8363 0.0521
-8.250 -0.3831 0.01410 0.00793 -0.1103 0.8235 0.0529
-8.000 -0.3576 0.01379 0.00751 -0.1096 0.8089 0.0537
-7.750 -0.3320 0.01351 0.00710 -0.1089 0.7934 0.0544
-7.500 -0.3068 0.01321 0.00675 -0.1081 0.7773 0.0554
-7.250 -0.2813 0.01300 0.00646 -0.1074 0.7602 0.0564
-7.000 -0.2557 0.01281 0.00616 -0.1067 0.7421 0.0574
-6.750 -0.2301 0.01262 0.00585 -0.1059 0.7234 0.0585
-6.500 -0.2046 0.01245 0.00554 -0.1052 0.7047 0.0595
-6.250 -0.1790 0.01227 0.00526 -0.1044 0.6878 0.0605
-6.000 -0.1529 0.01212 0.00505 -0.1038 0.6734 0.0618
-5.750 -0.1265 0.01200 0.00487 -0.1032 0.6622 0.0632
-5.500 -0.1000 0.01187 0.00466 -0.1027 0.6518 0.0647
-5.250 -0.0732 0.01173 0.00443 -0.1021 0.6431 0.0661
-5.000 -0.0464 0.01161 0.00428 -0.1016 0.6342 0.0675
-4.750 -0.0195 0.01152 0.00416 -0.1011 0.6266 0.0691
-4.500 0.0079 0.01142 0.00402 -0.1007 0.6199 0.0710
-4.250 0.0350 0.01133 0.00386 -0.1002 0.6131 0.0729
-4.000 0.0621 0.01127 0.00379 -0.0998 0.6062 0.0747
-3.750 0.0895 0.01121 0.00371 -0.0994 0.5980 0.0767
-3.500 0.1163 0.01118 0.00360 -0.0988 0.5894 0.0787
-3.250 0.1438 0.01110 0.00349 -0.0984 0.5821 0.0808
-3.000 0.1712 0.01106 0.00346 -0.0980 0.5755 0.0828
-2.750 0.1986 0.01105 0.00341 -0.0976 0.5700 0.0849
-2.500 0.2262 0.01100 0.00333 -0.0972 0.5655 0.0870
-2.250 0.2538 0.01093 0.00324 -0.0968 0.5601 0.0888
-2.000 0.2809 0.01089 0.00320 -0.0964 0.5527 0.0907
-1.750 0.3081 0.01089 0.00317 -0.0959 0.5459 0.0928
-1.500 0.3356 0.01085 0.00311 -0.0955 0.5387 0.0948
-1.250 0.3627 0.01084 0.00305 -0.0951 0.5318 0.0965
-1.000 0.3898 0.01079 0.00299 -0.0946 0.5255 0.0984
-0.750 0.4170 0.01072 0.00294 -0.0942 0.5192 0.1004
-0.500 0.4440 0.01070 0.00292 -0.0938 0.5128 0.1022
-0.250 0.4711 0.01069 0.00289 -0.0933 0.5073 0.1041
0.000 0.4985 0.01066 0.00287 -0.0929 0.5010 0.1060
0.250 0.5252 0.01069 0.00285 -0.0924 0.4930 0.1077
0.500 0.5519 0.01065 0.00281 -0.0919 0.4849 0.1096
0.750 0.5785 0.01062 0.00279 -0.0914 0.4763 0.1122
1.000 0.6050 0.01063 0.00280 -0.0909 0.4681 0.1142
1.250 0.6316 0.01065 0.00280 -0.0904 0.4589 0.1161
1.500 0.6578 0.01069 0.00282 -0.0898 0.4497 0.1182
1.750 0.6839 0.01075 0.00284 -0.0892 0.4381 0.1199
2.000 0.7098 0.01081 0.00287 -0.0886 0.4258 0.1219
2.250 0.7349 0.01089 0.00292 -0.0879 0.4104 0.1248
2.500 0.7596 0.01101 0.00300 -0.0871 0.3935 0.1282
2.750 0.7844 0.01115 0.00309 -0.0863 0.3788 0.1318
3.250 0.8340 0.01143 0.00330 -0.0848 0.3532 0.1421
3.750 0.8827 0.01169 0.00359 -0.0832 0.3317 0.1728
4.000 0.9063 0.01178 0.00379 -0.0824 0.3194 0.2321
4.250 0.9297 0.01190 0.00399 -0.0815 0.3085 0.2858
4.500 0.9530 0.01196 0.00418 -0.0806 0.2984 0.3507
5.000 1.0225 0.01133 0.00481 -0.0838 0.2710 1.0000
5.250 1.0442 0.01165 0.00503 -0.0826 0.2552 1.0000
5.500 1.0650 0.01201 0.00528 -0.0812 0.2360 1.0000
5.750 1.0836 0.01250 0.00561 -0.0796 0.2093 1.0000
6.000 1.0986 0.01318 0.00606 -0.0774 0.1729 1.0000
6.250 1.1147 0.01377 0.00650 -0.0753 0.1510 1.0000
6.500 1.1325 0.01424 0.00688 -0.0735 0.1404 1.0000
6.750 1.1521 0.01459 0.00721 -0.0720 0.1358 1.0000
7.000 1.1706 0.01497 0.00755 -0.0703 0.1316 1.0000
7.250 1.1868 0.01537 0.00792 -0.0682 0.1279 1.0000
7.500 1.2040 0.01569 0.00826 -0.0663 0.1257 1.0000
7.750 1.2208 0.01603 0.00861 -0.0643 0.1238 1.0000
8.000 1.2372 0.01641 0.00899 -0.0624 0.1221 1.0000
8.250 1.2531 0.01682 0.00941 -0.0604 0.1206 1.0000
8.500 1.2685 0.01727 0.00986 -0.0584 0.1191 1.0000
8.750 1.2830 0.01777 0.01037 -0.0564 0.1174 1.0000
9.000 1.2971 0.01831 0.01092 -0.0544 0.1160 1.0000
9.250 1.3111 0.01888 0.01151 -0.0524 0.1147 1.0000
9.500 1.3269 0.01937 0.01204 -0.0508 0.1139 1.0000
9.750 1.3424 0.01990 0.01262 -0.0492 0.1129 1.0000
10.000 1.3572 0.02050 0.01325 -0.0476 0.1119 1.0000
10.250 1.3712 0.02115 0.01394 -0.0460 0.1110 1.0000
10.500 1.3847 0.02186 0.01469 -0.0445 0.1098 1.0000
10.750 1.3975 0.02265 0.01551 -0.0429 0.1087 1.0000
11.000 1.4096 0.02351 0.01641 -0.0414 0.1074 1.0000
11.250 1.4204 0.02450 0.01743 -0.0399 0.1061 1.0000
11.500 1.4300 0.02561 0.01856 -0.0384 0.1049 1.0000
11.750 1.4381 0.02688 0.01987 -0.0369 0.1034 1.0000
12.000 1.4512 0.02783 0.02089 -0.0359 0.1026 1.0000
12.250 1.4641 0.02884 0.02195 -0.0350 0.1015 1.0000
12.500 1.4766 0.02990 0.02307 -0.0341 0.1002 1.0000
12.750 1.4881 0.03106 0.02429 -0.0332 0.0985 1.0000
13.000 1.4981 0.03240 0.02569 -0.0323 0.0970 1.0000
13.250 1.5067 0.03389 0.02722 -0.0315 0.0955 1.0000
13.500 1.5137 0.03558 0.02894 -0.0308 0.0940 1.0000
13.750 1.5202 0.03735 0.03076 -0.0301 0.0926 1.0000
14.000 1.5312 0.03875 0.03224 -0.0296 0.0912 1.0000
14.250 1.5409 0.04027 0.03384 -0.0291 0.0891 1.0000
14.500 1.5490 0.04198 0.03560 -0.0287 0.0864 1.0000
14.750 1.5546 0.04399 0.03764 -0.0283 0.0838 1.0000
15.000 1.5626 0.04577 0.03949 -0.0280 0.0801 1.0000
15.250 1.5673 0.04792 0.04166 -0.0277 0.0748 1.0000
15.500 1.5680 0.05055 0.04427 -0.0276 0.0668 1.0000
15.750 1.5640 0.05374 0.04743 -0.0275 0.0593 1.0000
16.000 1.5578 0.05723 0.05093 -0.0275 0.0537 1.0000
16.250 1.5510 0.06085 0.05458 -0.0276 0.0497 1.0000
16.500 1.5463 0.06432 0.05809 -0.0279 0.0470 1.0000
16.750 1.5413 0.06792 0.06175 -0.0282 0.0452 1.0000
17.000 1.5363 0.07157 0.06547 -0.0287 0.0437 1.0000
17.250 1.5320 0.07522 0.06919 -0.0293 0.0424 1.0000
17.500 1.5268 0.07904 0.07308 -0.0300 0.0412 1.0000
17.750 1.5207 0.08308 0.07719 -0.0308 0.0404 1.0000
18.000 1.5139 0.08727 0.08146 -0.0318 0.0395 1.0000
18.250 1.5096 0.09117 0.08546 -0.0328 0.0389 1.0000
18.500 1.5050 0.09518 0.08955 -0.0339 0.0383 1.0000
18.750 1.4988 0.09950 0.09396 -0.0352 0.0376 1.0000
19.000 1.4922 0.10392 0.09846 -0.0367 0.0371 1.0000
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