GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 200,000 Max Cl/Cd: 88.17 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe450-il-200000.txt Download as CSV file: xf-goe450-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3432 0.10215 0.09881 -0.0282 1.0000 0.0381
-8.000 -0.3590 0.10136 0.09810 -0.0259 1.0000 0.0386
-7.750 -0.3792 0.10095 0.09778 -0.0231 1.0000 0.0389
-7.500 -0.3539 0.09602 0.09283 -0.0404 0.9920 0.0395
-7.250 -0.3431 0.09044 0.08726 -0.0396 0.9893 0.0403
-7.000 -0.3249 0.08717 0.08398 -0.0387 0.9869 0.0417
-6.750 -0.2981 0.08306 0.07984 -0.0446 0.9836 0.0437
-6.500 -0.2758 0.07891 0.07566 -0.0512 0.9763 0.0460
-6.250 -0.2192 0.07084 0.06735 -0.0770 0.9674 0.0495
-6.000 -0.2096 0.06717 0.06376 -0.0743 0.9630 0.0505
-5.750 -0.1853 0.06428 0.06084 -0.0758 0.9597 0.0524
-5.500 -0.1250 0.05918 0.05527 -0.0935 0.9523 0.0605
-5.250 -0.1078 0.05373 0.04992 -0.0950 0.9475 0.0619
-5.000 -0.0801 0.05109 0.04731 -0.0968 0.9447 0.0640
-4.750 -0.0385 0.04759 0.04365 -0.1031 0.9425 0.0698
-4.500 -0.0059 0.04305 0.03880 -0.1084 0.9338 0.0757
-4.250 0.0274 0.04085 0.03660 -0.1111 0.9307 0.0804
-4.000 0.0745 0.03676 0.03210 -0.1178 0.9284 0.0902
-3.750 0.1017 0.03482 0.03015 -0.1189 0.9222 0.0943
-3.500 0.1383 0.03210 0.02707 -0.1220 0.9168 0.1054
-3.250 0.1776 0.03021 0.02487 -0.1251 0.9137 0.1192
-3.000 0.2035 0.02832 0.02308 -0.1255 0.9070 0.1249
-2.750 0.2358 0.02655 0.02113 -0.1269 0.9011 0.1386
-2.500 0.2711 0.02490 0.01935 -0.1287 0.8976 0.1547
-2.250 0.3130 0.01942 0.01243 -0.1279 0.8898 0.0681
-2.000 0.3462 0.01809 0.01085 -0.1284 0.8844 0.0676
-1.750 0.3752 0.01702 0.00956 -0.1281 0.8766 0.0665
-1.500 0.4057 0.01599 0.00837 -0.1280 0.8696 0.0654
-1.250 0.4337 0.01524 0.00755 -0.1275 0.8612 0.0655
-1.000 0.4631 0.01453 0.00680 -0.1273 0.8538 0.0664
-0.750 0.4898 0.01403 0.00629 -0.1267 0.8440 0.0680
-0.500 0.5196 0.01353 0.00575 -0.1266 0.8370 0.0713
-0.250 0.5455 0.01316 0.00540 -0.1260 0.8261 0.0756
0.000 0.5732 0.01282 0.00506 -0.1257 0.8170 0.0818
0.250 0.6017 0.01247 0.00471 -0.1255 0.8082 0.0973
0.500 0.6268 0.01019 0.00470 -0.1249 0.7986 1.0000
0.750 0.6550 0.01020 0.00451 -0.1246 0.7898 1.0000
1.000 0.6821 0.01026 0.00444 -0.1242 0.7795 1.0000
1.250 0.7089 0.01034 0.00441 -0.1238 0.7691 1.0000
1.500 0.7367 0.01040 0.00436 -0.1236 0.7598 1.0000
1.750 0.7636 0.01050 0.00438 -0.1232 0.7493 1.0000
2.000 0.7902 0.01062 0.00443 -0.1228 0.7386 1.0000
2.250 0.8175 0.01073 0.00446 -0.1226 0.7286 1.0000
2.500 0.8444 0.01085 0.00451 -0.1222 0.7178 1.0000
2.750 0.8705 0.01099 0.00461 -0.1218 0.7059 1.0000
3.000 0.8968 0.01114 0.00472 -0.1213 0.6938 1.0000
3.250 0.9231 0.01129 0.00482 -0.1209 0.6817 1.0000
3.500 0.9495 0.01145 0.00492 -0.1204 0.6695 1.0000
3.750 0.9755 0.01163 0.00503 -0.1199 0.6562 1.0000
4.000 1.0007 0.01180 0.00520 -0.1193 0.6418 1.0000
4.250 1.0256 0.01198 0.00533 -0.1186 0.6262 1.0000
4.500 1.0502 0.01217 0.00549 -0.1178 0.6099 1.0000
4.750 1.0745 0.01237 0.00569 -0.1170 0.5934 1.0000
5.000 1.0984 0.01257 0.00589 -0.1162 0.5760 1.0000
5.250 1.1215 0.01276 0.00607 -0.1152 0.5556 1.0000
5.500 1.1446 0.01299 0.00627 -0.1142 0.5360 1.0000
5.750 1.1674 0.01324 0.00652 -0.1132 0.5160 1.0000
6.000 1.1898 0.01352 0.00679 -0.1122 0.4948 1.0000
6.250 1.2113 0.01386 0.00708 -0.1110 0.4722 1.0000
6.500 1.2313 0.01426 0.00741 -0.1096 0.4452 1.0000
6.750 1.2515 0.01469 0.00782 -0.1082 0.4192 1.0000
7.000 1.2693 0.01524 0.00827 -0.1065 0.3870 1.0000
7.250 1.2842 0.01595 0.00881 -0.1043 0.3432 1.0000
7.500 1.2942 0.01697 0.00953 -0.1014 0.2778 1.0000
7.750 1.2891 0.01916 0.01090 -0.0966 0.1606 1.0000
8.000 1.2838 0.02138 0.01252 -0.0917 0.0836 1.0000
8.250 1.2889 0.02275 0.01385 -0.0882 0.0683 1.0000
8.500 1.2951 0.02406 0.01517 -0.0851 0.0611 1.0000
8.750 1.3050 0.02515 0.01635 -0.0825 0.0565 1.0000
9.000 1.3131 0.02638 0.01762 -0.0800 0.0525 1.0000
9.250 1.3151 0.02809 0.01935 -0.0768 0.0497 1.0000
9.500 1.3228 0.02946 0.02086 -0.0744 0.0477 1.0000
9.750 1.3294 0.03098 0.02246 -0.0720 0.0456 1.0000
10.000 1.3355 0.03259 0.02412 -0.0697 0.0436 1.0000
10.250 1.3389 0.03459 0.02612 -0.0672 0.0416 1.0000
10.500 1.3461 0.03656 0.02813 -0.0650 0.0401 1.0000
10.750 1.3583 0.03810 0.02979 -0.0632 0.0389 1.0000
11.000 1.3718 0.03970 0.03150 -0.0616 0.0376 1.0000
11.250 1.3850 0.04132 0.03321 -0.0600 0.0360 1.0000
11.500 1.3985 0.04303 0.03496 -0.0587 0.0344 1.0000
11.750 1.4437 0.04661 0.03855 -0.0597 0.0323 1.0000
12.000 1.4506 0.04851 0.04070 -0.0576 0.0319 1.0000
12.250 1.4576 0.05078 0.04325 -0.0556 0.0314 1.0000
12.500 1.4610 0.05321 0.04596 -0.0535 0.0309 1.0000
12.750 1.4612 0.05583 0.04886 -0.0513 0.0303 1.0000
13.000 1.4591 0.05869 0.05197 -0.0493 0.0297 1.0000
13.250 1.4545 0.06182 0.05537 -0.0473 0.0292 1.0000
13.500 1.4470 0.06545 0.05928 -0.0455 0.0291 1.0000
13.750 1.4357 0.06952 0.06363 -0.0440 0.0291 1.0000
14.000 1.4214 0.07398 0.06837 -0.0428 0.0292 1.0000
14.250 1.4046 0.07885 0.07352 -0.0421 0.0294 1.0000
14.500 1.3855 0.08412 0.07905 -0.0420 0.0296 1.0000
14.750 1.3647 0.08982 0.08500 -0.0426 0.0299 1.0000
15.000 1.3428 0.09591 0.09132 -0.0439 0.0302 1.0000
15.250 1.3204 0.10249 0.09810 -0.0460 0.0305 1.0000
15.500 1.2977 0.10960 0.10541 -0.0490 0.0309 1.0000
15.750 1.2754 0.11719 0.11318 -0.0526 0.0312 1.0000
16.000 1.2541 0.12528 0.12141 -0.0566 0.0317 1.0000
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Polar data table (+)
Polar graphs
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