GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 496 AIRFOIL (goe496-il) Reynolds number: 200,000 Max Cl/Cd: 89.6 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe496-il-200000.txt Download as CSV file: xf-goe496-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 496 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3306 0.10335 0.09983 -0.0366 1.0000 0.0655
-8.750 -0.3585 0.10233 0.09894 -0.0370 1.0000 0.0663
-8.500 -0.3825 0.10141 0.09812 -0.0353 1.0000 0.0665
-8.250 -0.3653 0.09693 0.09364 -0.0321 1.0000 0.0679
-8.000 -0.3605 0.09548 0.09222 -0.0288 1.0000 0.0692
-7.750 -0.3682 0.09441 0.09120 -0.0259 1.0000 0.0703
-7.500 -0.3518 0.09117 0.08795 -0.0299 0.9963 0.0734
-7.250 -0.3392 0.08252 0.07932 -0.0520 0.9838 0.0788
-7.000 -0.3181 0.08058 0.07736 -0.0483 0.9814 0.0802
-6.750 -0.2936 0.07842 0.07517 -0.0490 0.9765 0.0836
-6.500 -0.2632 0.06820 0.06488 -0.0740 0.9642 0.0917
-6.250 -0.2253 0.03923 0.03494 -0.1100 0.9571 0.0676
-6.000 -0.1981 0.03419 0.02948 -0.1141 0.9492 0.0656
-5.750 -0.1603 0.02831 0.02296 -0.1202 0.9457 0.0643
-5.500 -0.1192 0.02448 0.01848 -0.1248 0.9434 0.0644
-5.250 -0.0876 0.02267 0.01623 -0.1262 0.9372 0.0658
-5.000 -0.0512 0.02099 0.01418 -0.1282 0.9327 0.0668
-4.750 -0.0120 0.01910 0.01207 -0.1309 0.9301 0.0685
-4.500 0.0299 0.01806 0.01096 -0.1337 0.9282 0.0709
-4.250 0.0590 0.01748 0.01030 -0.1339 0.9207 0.0741
-4.000 0.0981 0.01670 0.00937 -0.1359 0.9171 0.0777
-3.750 0.1382 0.01578 0.00849 -0.1382 0.9144 0.0822
-3.500 0.1726 0.01528 0.00795 -0.1392 0.9090 0.0884
-3.250 0.2052 0.01477 0.00746 -0.1400 0.9026 0.0980
-3.000 0.2439 0.01419 0.00686 -0.1418 0.8989 0.1195
-2.750 0.2738 0.01369 0.00644 -0.1421 0.8914 0.1501
-2.500 0.3076 0.01328 0.00608 -0.1432 0.8855 0.1721
-2.250 0.3410 0.01297 0.00579 -0.1440 0.8794 0.1894
-2.000 0.3705 0.01274 0.00557 -0.1441 0.8711 0.2049
-1.750 0.4034 0.01247 0.00533 -0.1448 0.8647 0.2246
-1.500 0.4317 0.01226 0.00522 -0.1447 0.8555 0.2497
-1.250 0.4620 0.01203 0.00509 -0.1449 0.8476 0.2916
-1.000 0.4910 0.01179 0.00502 -0.1449 0.8388 0.3475
-0.750 0.5188 0.01168 0.00501 -0.1446 0.8295 0.3944
-0.500 0.5489 0.01156 0.00492 -0.1447 0.8214 0.4334
-0.250 0.5751 0.01152 0.00494 -0.1442 0.8109 0.4671
0.000 0.6038 0.01142 0.00488 -0.1440 0.8025 0.5020
0.250 0.6302 0.01131 0.00489 -0.1435 0.7923 0.5417
0.500 0.6561 0.01118 0.00496 -0.1428 0.7826 0.5992
0.750 0.6820 0.01093 0.00493 -0.1419 0.7738 0.6967
1.000 0.7081 0.01041 0.00485 -0.1408 0.7622 1.0000
1.250 0.7355 0.01051 0.00482 -0.1404 0.7508 1.0000
1.500 0.7635 0.01059 0.00477 -0.1401 0.7398 1.0000
1.750 0.7905 0.01069 0.00477 -0.1396 0.7281 1.0000
2.000 0.8166 0.01080 0.00481 -0.1390 0.7156 1.0000
2.250 0.8431 0.01090 0.00484 -0.1385 0.7034 1.0000
2.500 0.8700 0.01102 0.00488 -0.1380 0.6922 1.0000
2.750 0.8967 0.01116 0.00496 -0.1376 0.6814 1.0000
3.000 0.9227 0.01132 0.00510 -0.1370 0.6704 1.0000
3.250 0.9494 0.01148 0.00521 -0.1366 0.6602 1.0000
3.500 0.9760 0.01163 0.00532 -0.1361 0.6495 1.0000
3.750 1.0013 0.01179 0.00549 -0.1355 0.6377 1.0000
4.000 1.0273 0.01197 0.00566 -0.1349 0.6269 1.0000
4.250 1.0535 0.01216 0.00581 -0.1344 0.6159 1.0000
4.500 1.0787 0.01233 0.00598 -0.1337 0.6035 1.0000
4.750 1.1034 0.01252 0.00619 -0.1329 0.5905 1.0000
5.000 1.1282 0.01273 0.00641 -0.1321 0.5776 1.0000
5.250 1.1528 0.01294 0.00663 -0.1313 0.5640 1.0000
5.500 1.1767 0.01316 0.00685 -0.1304 0.5489 1.0000
5.750 1.2001 0.01340 0.00710 -0.1294 0.5326 1.0000
6.000 1.2230 0.01365 0.00737 -0.1282 0.5150 1.0000
6.250 1.2442 0.01395 0.00760 -0.1268 0.4929 1.0000
6.500 1.2630 0.01426 0.00786 -0.1249 0.4630 1.0000
6.750 1.2802 0.01466 0.00818 -0.1228 0.4267 1.0000
7.000 1.2955 0.01523 0.00857 -0.1205 0.3865 1.0000
7.250 1.3099 0.01592 0.00906 -0.1182 0.3465 1.0000
7.500 1.3235 0.01671 0.00965 -0.1158 0.3125 1.0000
7.750 1.3381 0.01748 0.01029 -0.1136 0.2861 1.0000
8.000 1.3523 0.01827 0.01098 -0.1114 0.2652 1.0000
8.250 1.3674 0.01899 0.01166 -0.1094 0.2465 1.0000
8.500 1.3813 0.01970 0.01235 -0.1072 0.2278 1.0000
8.750 1.3931 0.02045 0.01307 -0.1046 0.2086 1.0000
9.000 1.4037 0.02125 0.01383 -0.1020 0.1852 1.0000
9.250 1.4096 0.02235 0.01476 -0.0988 0.1426 1.0000
9.500 1.4030 0.02443 0.01636 -0.0942 0.0876 1.0000
9.750 1.3986 0.02652 0.01827 -0.0902 0.0670 1.0000
10.000 1.3963 0.02852 0.02023 -0.0866 0.0577 1.0000
10.250 1.3993 0.03021 0.02200 -0.0839 0.0519 1.0000
10.500 1.3959 0.03248 0.02427 -0.0808 0.0481 1.0000
10.750 1.4016 0.03415 0.02607 -0.0788 0.0447 1.0000
11.000 1.4047 0.03609 0.02805 -0.0768 0.0420 1.0000
11.250 1.4018 0.03877 0.03074 -0.0745 0.0400 1.0000
11.500 1.4081 0.04070 0.03279 -0.0729 0.0385 1.0000
11.750 1.4145 0.04270 0.03490 -0.0714 0.0370 1.0000
12.000 1.4211 0.04474 0.03701 -0.0700 0.0355 1.0000
12.250 1.4276 0.04683 0.03914 -0.0688 0.0341 1.0000
12.500 1.4385 0.04929 0.04153 -0.0674 0.0323 1.0000
12.750 1.4456 0.05130 0.04373 -0.0664 0.0314 1.0000
13.000 1.4552 0.05342 0.04602 -0.0653 0.0305 1.0000
13.250 1.4650 0.05565 0.04839 -0.0643 0.0297 1.0000
13.500 1.4742 0.05798 0.05086 -0.0634 0.0289 1.0000
13.750 1.4821 0.06049 0.05351 -0.0625 0.0282 1.0000
14.000 1.4890 0.06310 0.05622 -0.0618 0.0276 1.0000
14.250 1.4989 0.06576 0.05894 -0.0612 0.0268 1.0000
14.500 1.5084 0.06974 0.06310 -0.0605 0.0260 1.0000
14.750 1.4991 0.07347 0.06711 -0.0602 0.0258 1.0000
15.000 1.4895 0.07759 0.07150 -0.0602 0.0256 1.0000
15.250 1.4791 0.08211 0.07629 -0.0606 0.0254 1.0000
15.500 1.4675 0.08709 0.08153 -0.0614 0.0252 1.0000
15.750 1.4542 0.09249 0.08719 -0.0627 0.0252 1.0000
16.000 1.4392 0.09837 0.09332 -0.0645 0.0252 1.0000
16.250 1.4229 0.10470 0.09990 -0.0670 0.0252 1.0000
16.500 1.4052 0.11151 0.10694 -0.0701 0.0252 1.0000
16.750 1.3869 0.11879 0.11445 -0.0739 0.0253 1.0000
17.000 1.3677 0.12659 0.12247 -0.0784 0.0254 1.0000
17.250 1.3485 0.13483 0.13090 -0.0835 0.0256 1.0000
17.500 1.3285 0.14370 0.13994 -0.0893 0.0258 1.0000
17.750 1.3095 0.15286 0.14926 -0.0954 0.0260 1.0000
18.000 1.2926 0.16205 0.15862 -0.1019 0.0263 1.0000
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Polar data table (+)
Polar graphs
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