GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.93 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe534-il-1000000.txt Download as CSV file: xf-goe534-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7681 0.09112 0.08854 -0.0462 1.0000 0.0269
-15.750 -0.7973 0.08248 0.07978 -0.0520 1.0000 0.0271
-15.500 -0.8187 0.07549 0.07268 -0.0567 1.0000 0.0271
-15.250 -0.8382 0.06898 0.06609 -0.0612 1.0000 0.0273
-15.000 -0.8550 0.06318 0.06020 -0.0652 1.0000 0.0274
-14.750 -0.8738 0.05759 0.05453 -0.0691 1.0000 0.0274
-14.500 -0.8933 0.05213 0.04898 -0.0729 1.0000 0.0275
-14.250 -0.9146 0.04698 0.04375 -0.0762 1.0000 0.0275
-14.000 -0.9528 0.04142 0.03812 -0.0785 1.0000 0.0275
-13.750 -0.9679 0.03581 0.03240 -0.0837 1.0000 0.0276
-13.500 -0.9667 0.03122 0.02766 -0.0884 1.0000 0.0277
-13.250 -0.9539 0.02767 0.02397 -0.0922 1.0000 0.0279
-13.000 -0.9369 0.02559 0.02176 -0.0937 1.0000 0.0280
-12.750 -0.9234 0.02388 0.01993 -0.0936 1.0000 0.0282
-12.500 -0.9114 0.02211 0.01808 -0.0930 1.0000 0.0286
-12.250 -0.8959 0.02087 0.01678 -0.0921 1.0000 0.0289
-12.000 -0.8646 0.01976 0.01562 -0.0938 0.9986 0.0293
-11.750 -0.8278 0.01879 0.01459 -0.0963 0.9961 0.0296
-11.500 -0.7904 0.01794 0.01368 -0.0987 0.9935 0.0301
-11.250 -0.7560 0.01717 0.01285 -0.1003 0.9900 0.0306
-11.000 -0.7220 0.01648 0.01210 -0.1018 0.9858 0.0310
-10.750 -0.6862 0.01582 0.01138 -0.1035 0.9822 0.0314
-10.500 -0.6534 0.01524 0.01074 -0.1044 0.9768 0.0317
-10.250 -0.6200 0.01454 0.00997 -0.1056 0.9693 0.0321
-10.000 -0.5849 0.01366 0.00904 -0.1073 0.9603 0.0328
-9.750 -0.5459 0.01300 0.00833 -0.1096 0.9480 0.0334
-9.500 -0.5071 0.01248 0.00772 -0.1116 0.9233 0.0341
-9.250 -0.4765 0.01214 0.00722 -0.1118 0.8862 0.0347
-9.000 -0.4510 0.01190 0.00681 -0.1110 0.8532 0.0353
-8.750 -0.4257 0.01168 0.00644 -0.1101 0.8283 0.0358
-8.500 -0.4005 0.01135 0.00599 -0.1092 0.8088 0.0365
-8.250 -0.3749 0.01101 0.00557 -0.1085 0.7935 0.0376
-8.000 -0.3488 0.01074 0.00522 -0.1078 0.7804 0.0386
-7.750 -0.3219 0.01049 0.00490 -0.1072 0.7687 0.0397
-7.500 -0.2952 0.01024 0.00459 -0.1066 0.7577 0.0413
-7.250 -0.2683 0.00996 0.00428 -0.1060 0.7471 0.0443
-7.000 -0.2414 0.00972 0.00406 -0.1055 0.7377 0.0514
-6.750 -0.2131 0.00967 0.00405 -0.1050 0.7279 0.0612
-6.500 -0.1848 0.00971 0.00408 -0.1045 0.7180 0.0659
-6.250 -0.1559 0.00978 0.00409 -0.1041 0.7077 0.0685
-6.000 -0.1281 0.00971 0.00400 -0.1037 0.6978 0.0712
-5.750 -0.0996 0.00971 0.00398 -0.1032 0.6864 0.0732
-5.500 -0.0714 0.00972 0.00393 -0.1028 0.6746 0.0748
-5.250 -0.0431 0.00978 0.00390 -0.1023 0.6608 0.0758
-5.000 -0.0161 0.00954 0.00363 -0.1018 0.6453 0.0777
-4.750 0.0114 0.00947 0.00351 -0.1013 0.6271 0.0793
-4.500 0.0389 0.00947 0.00343 -0.1007 0.6060 0.0809
-4.250 0.0660 0.00948 0.00333 -0.1001 0.5824 0.0822
-4.000 0.0933 0.00950 0.00324 -0.0995 0.5592 0.0832
-3.750 0.1207 0.00954 0.00318 -0.0990 0.5395 0.0840
-3.500 0.1479 0.00951 0.00305 -0.0984 0.5234 0.0848
-3.250 0.1752 0.00935 0.00284 -0.0979 0.5112 0.0864
-3.000 0.2028 0.00927 0.00273 -0.0975 0.5009 0.0876
-2.750 0.2306 0.00923 0.00264 -0.0970 0.4911 0.0888
-2.500 0.2585 0.00920 0.00257 -0.0966 0.4820 0.0902
-2.250 0.2865 0.00916 0.00250 -0.0962 0.4729 0.0913
-2.000 0.3143 0.00915 0.00244 -0.0958 0.4647 0.0923
-1.750 0.3426 0.00912 0.00239 -0.0954 0.4575 0.0934
-1.500 0.3703 0.00911 0.00232 -0.0949 0.4491 0.0946
-1.250 0.3984 0.00903 0.00223 -0.0945 0.4421 0.0964
-1.000 0.4263 0.00900 0.00217 -0.0941 0.4342 0.0981
-0.750 0.4541 0.00900 0.00214 -0.0937 0.4269 0.0999
-0.500 0.4823 0.00897 0.00211 -0.0933 0.4204 0.1018
-0.250 0.5101 0.00900 0.00209 -0.0929 0.4130 0.1039
0.000 0.5379 0.00897 0.00207 -0.0925 0.4062 0.1098
0.250 0.5656 0.00892 0.00205 -0.0921 0.3986 0.1244
0.500 0.5921 0.00874 0.00206 -0.0916 0.3906 0.1971
0.750 0.6198 0.00864 0.00209 -0.0913 0.3845 0.2408
1.000 0.6471 0.00865 0.00215 -0.0908 0.3768 0.2694
1.250 0.6746 0.00868 0.00221 -0.0904 0.3694 0.2918
1.500 0.7021 0.00872 0.00227 -0.0900 0.3611 0.3127
1.750 0.7292 0.00879 0.00235 -0.0895 0.3530 0.3303
2.000 0.7568 0.00884 0.00243 -0.0891 0.3453 0.3477
2.250 0.7836 0.00896 0.00252 -0.0886 0.3360 0.3629
2.500 0.8110 0.00903 0.00260 -0.0882 0.3276 0.3772
2.750 0.8376 0.00916 0.00271 -0.0877 0.3181 0.3916
3.000 0.8647 0.00925 0.00281 -0.0872 0.3091 0.4060
3.500 0.9177 0.00953 0.00306 -0.0862 0.2899 0.4326
3.750 0.9440 0.00968 0.00319 -0.0856 0.2811 0.4451
4.000 0.9702 0.00985 0.00333 -0.0850 0.2721 0.4574
4.250 0.9963 0.00999 0.00348 -0.0845 0.2642 0.4698
4.500 1.0223 0.01015 0.00363 -0.0839 0.2567 0.4839
4.750 1.0479 0.01032 0.00380 -0.0833 0.2498 0.5003
5.000 1.0739 0.01045 0.00395 -0.0827 0.2440 0.5170
5.250 1.0989 0.01063 0.00415 -0.0820 0.2371 0.5382
5.500 1.1242 0.01073 0.00432 -0.0813 0.2325 0.5700
5.750 1.1479 0.01069 0.00452 -0.0804 0.2280 0.6652
6.000 1.1960 0.01048 0.00483 -0.0848 0.2207 1.0000
6.250 1.2215 0.01066 0.00500 -0.0842 0.2170 1.0000
6.500 1.2470 0.01085 0.00518 -0.0835 0.2133 1.0000
6.750 1.2716 0.01109 0.00538 -0.0828 0.2090 1.0000
7.000 1.2952 0.01139 0.00564 -0.0819 0.2037 1.0000
7.250 1.3207 0.01155 0.00581 -0.0813 0.2011 1.0000
7.500 1.3454 0.01175 0.00601 -0.0806 0.1974 1.0000
7.750 1.3690 0.01202 0.00624 -0.0798 0.1928 1.0000
8.000 1.3920 0.01233 0.00652 -0.0788 0.1881 1.0000
8.250 1.4166 0.01251 0.00672 -0.0782 0.1852 1.0000
8.500 1.4402 0.01274 0.00695 -0.0773 0.1816 1.0000
8.750 1.4625 0.01305 0.00723 -0.0763 0.1772 1.0000
9.000 1.4847 0.01335 0.00752 -0.0753 0.1733 1.0000
9.250 1.5080 0.01358 0.00776 -0.0744 0.1705 1.0000
9.500 1.5300 0.01386 0.00803 -0.0734 0.1668 1.0000
9.750 1.5504 0.01422 0.00837 -0.0721 0.1625 1.0000
10.000 1.5712 0.01453 0.00869 -0.0709 0.1591 1.0000
10.250 1.5922 0.01481 0.00898 -0.0698 0.1557 1.0000
10.500 1.6111 0.01518 0.00933 -0.0683 0.1516 1.0000
10.750 1.6263 0.01561 0.00975 -0.0662 0.1472 1.0000
11.000 1.6439 0.01591 0.01008 -0.0645 0.1447 1.0000
11.250 1.6596 0.01629 0.01047 -0.0625 0.1414 1.0000
11.500 1.6734 0.01678 0.01095 -0.0604 0.1376 1.0000
11.750 1.6873 0.01728 0.01146 -0.0583 0.1342 1.0000
12.000 1.7031 0.01772 0.01193 -0.0566 0.1316 1.0000
12.250 1.7167 0.01828 0.01250 -0.0548 0.1284 1.0000
12.500 1.7280 0.01900 0.01322 -0.0527 0.1249 1.0000
12.750 1.7407 0.01968 0.01393 -0.0510 0.1223 1.0000
13.000 1.7542 0.02035 0.01464 -0.0495 0.1198 1.0000
13.250 1.7655 0.02120 0.01550 -0.0479 0.1170 1.0000
13.500 1.7737 0.02232 0.01663 -0.0463 0.1136 1.0000
13.750 1.7846 0.02332 0.01768 -0.0450 0.1111 1.0000
14.000 1.7957 0.02439 0.01878 -0.0439 0.1085 1.0000
14.250 1.8037 0.02574 0.02016 -0.0428 0.1056 1.0000
14.500 1.8084 0.02747 0.02191 -0.0418 0.1026 1.0000
14.750 1.8177 0.02886 0.02336 -0.0411 0.1006 1.0000
15.000 1.8254 0.03044 0.02499 -0.0404 0.0987 1.0000
15.250 1.8301 0.03234 0.02693 -0.0398 0.0965 1.0000
15.500 1.8312 0.03463 0.02926 -0.0392 0.0942 1.0000
15.750 1.8312 0.03708 0.03177 -0.0388 0.0921 1.0000
16.000 1.8355 0.03914 0.03390 -0.0384 0.0905 1.0000
16.250 1.8362 0.04162 0.03644 -0.0382 0.0888 1.0000
16.500 1.8327 0.04459 0.03947 -0.0380 0.0868 1.0000
16.750 1.8267 0.04796 0.04290 -0.0381 0.0852 1.0000
17.000 1.8168 0.05189 0.04690 -0.0384 0.0834 1.0000
17.250 1.8146 0.05498 0.05009 -0.0387 0.0824 1.0000
17.500 1.8097 0.05846 0.05365 -0.0391 0.0813 1.0000
17.750 1.8015 0.06237 0.05764 -0.0397 0.0798 1.0000
18.000 1.7906 0.06666 0.06200 -0.0404 0.0787 1.0000
18.250 1.7763 0.07144 0.06686 -0.0413 0.0774 1.0000
18.500 1.7599 0.07653 0.07203 -0.0424 0.0763 1.0000
18.750 1.7430 0.08177 0.07735 -0.0436 0.0752 1.0000
19.000 1.7343 0.08597 0.08164 -0.0446 0.0744 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 534 AIRFOIL (goe534-il)