GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.82 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe535-il-1000000.txt Download as CSV file: xf-goe535-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7951 0.07443 0.07150 -0.0819 1.0000 0.0318
-16.250 -0.8236 0.06737 0.06433 -0.0862 1.0000 0.0320
-16.000 -0.8428 0.06198 0.05885 -0.0891 1.0000 0.0321
-15.750 -0.8636 0.05678 0.05357 -0.0918 1.0000 0.0321
-15.500 -0.8815 0.05244 0.04917 -0.0935 1.0000 0.0323
-15.250 -0.9014 0.04850 0.04516 -0.0946 1.0000 0.0323
-15.000 -0.9244 0.04490 0.04150 -0.0947 1.0000 0.0324
-14.750 -0.9520 0.04170 0.03825 -0.0937 1.0000 0.0325
-14.500 -0.9429 0.03782 0.03430 -0.0997 0.9973 0.0327
-14.250 -0.9291 0.03409 0.03048 -0.1066 0.9931 0.0328
-14.000 -0.9096 0.03077 0.02708 -0.1127 0.9887 0.0332
-13.750 -0.8839 0.02779 0.02401 -0.1190 0.9849 0.0334
-13.500 -0.8517 0.02526 0.02138 -0.1253 0.9826 0.0338
-13.250 -0.8162 0.02311 0.01912 -0.1311 0.9810 0.0341
-13.000 -0.7805 0.02159 0.01750 -0.1354 0.9799 0.0345
-12.750 -0.7566 0.02051 0.01634 -0.1364 0.9749 0.0348
-12.500 -0.7253 0.01956 0.01531 -0.1383 0.9721 0.0351
-12.250 -0.6916 0.01874 0.01442 -0.1404 0.9701 0.0353
-12.000 -0.6572 0.01741 0.01303 -0.1433 0.9681 0.0360
-11.750 -0.6188 0.01650 0.01210 -0.1462 0.9661 0.0366
-11.500 -0.5923 0.01588 0.01143 -0.1463 0.9588 0.0370
-11.250 -0.5596 0.01531 0.01083 -0.1476 0.9539 0.0376
-11.000 -0.5240 0.01477 0.01025 -0.1493 0.9500 0.0383
-10.750 -0.4996 0.01436 0.00979 -0.1487 0.9409 0.0389
-10.500 -0.4673 0.01393 0.00928 -0.1496 0.9344 0.0394
-10.250 -0.4422 0.01339 0.00869 -0.1492 0.9240 0.0400
-10.000 -0.4141 0.01287 0.00813 -0.1494 0.9138 0.0409
-9.750 -0.3873 0.01253 0.00773 -0.1491 0.9007 0.0416
-9.500 -0.3605 0.01224 0.00739 -0.1488 0.8874 0.0424
-9.250 -0.3336 0.01198 0.00704 -0.1484 0.8725 0.0433
-9.000 -0.3073 0.01177 0.00673 -0.1478 0.8547 0.0440
-8.750 -0.2826 0.01142 0.00629 -0.1471 0.8351 0.0452
-8.500 -0.2572 0.01123 0.00603 -0.1463 0.8146 0.0464
-8.250 -0.2316 0.01110 0.00580 -0.1456 0.7949 0.0476
-8.000 -0.2059 0.01100 0.00559 -0.1449 0.7761 0.0487
-7.500 -0.1544 0.01068 0.00514 -0.1435 0.7416 0.0517
-7.250 -0.1279 0.01062 0.00500 -0.1429 0.7264 0.0533
-7.000 -0.1017 0.01051 0.00481 -0.1423 0.7122 0.0549
-6.750 -0.0750 0.01038 0.00465 -0.1417 0.6994 0.0565
-6.500 -0.0479 0.01033 0.00454 -0.1412 0.6879 0.0582
-6.250 -0.0208 0.01030 0.00444 -0.1407 0.6755 0.0597
-6.000 0.0060 0.01013 0.00423 -0.1402 0.6644 0.0614
-5.500 0.0605 0.01003 0.00404 -0.1393 0.6418 0.0646
-5.000 0.1148 0.00985 0.00377 -0.1384 0.6209 0.0679
-4.750 0.1415 0.00982 0.00368 -0.1378 0.6094 0.0695
-4.500 0.1693 0.00975 0.00359 -0.1374 0.5987 0.0712
-4.250 0.1963 0.00975 0.00351 -0.1369 0.5873 0.0725
-4.000 0.2235 0.00962 0.00334 -0.1365 0.5766 0.0741
-3.750 0.2502 0.00954 0.00322 -0.1359 0.5656 0.0760
-3.500 0.2775 0.00951 0.00315 -0.1355 0.5537 0.0778
-3.250 0.3046 0.00949 0.00307 -0.1350 0.5421 0.0795
-3.000 0.3316 0.00952 0.00303 -0.1345 0.5297 0.0807
-2.750 0.3584 0.00938 0.00286 -0.1340 0.5192 0.0835
-2.500 0.3849 0.00938 0.00280 -0.1334 0.5073 0.0855
-2.250 0.4124 0.00936 0.00274 -0.1330 0.4972 0.0875
-2.000 0.4391 0.00939 0.00270 -0.1325 0.4863 0.0889
-1.750 0.4662 0.00931 0.00260 -0.1320 0.4778 0.0921
-1.500 0.4927 0.00932 0.00256 -0.1315 0.4684 0.0949
-1.250 0.5203 0.00931 0.00253 -0.1311 0.4614 0.0975
-1.000 0.5471 0.00930 0.00249 -0.1306 0.4537 0.1018
-0.750 0.5738 0.00930 0.00247 -0.1301 0.4467 0.1075
-0.250 0.6269 0.00900 0.00241 -0.1291 0.4352 0.1918
0.000 0.6513 0.00872 0.00241 -0.1285 0.4284 0.3042
0.250 0.6787 0.00866 0.00248 -0.1281 0.4246 0.3541
0.500 0.7060 0.00871 0.00255 -0.1277 0.4197 0.3729
0.750 0.7327 0.00880 0.00262 -0.1271 0.4143 0.3859
1.000 0.7590 0.00891 0.00271 -0.1266 0.4084 0.3957
1.250 0.7867 0.00895 0.00277 -0.1262 0.4042 0.4057
1.500 0.8136 0.00903 0.00283 -0.1257 0.3987 0.4145
1.750 0.8397 0.00914 0.00292 -0.1251 0.3930 0.4219
2.000 0.8663 0.00925 0.00302 -0.1246 0.3886 0.4291
2.250 0.8936 0.00930 0.00308 -0.1242 0.3850 0.4358
2.500 0.9202 0.00938 0.00317 -0.1237 0.3808 0.4438
2.750 0.9462 0.00949 0.00326 -0.1231 0.3762 0.4496
3.000 0.9715 0.00965 0.00338 -0.1224 0.3711 0.4549
3.250 0.9984 0.00969 0.00347 -0.1219 0.3684 0.4631
3.500 1.0249 0.00977 0.00356 -0.1214 0.3646 0.4696
3.750 1.0508 0.00989 0.00366 -0.1208 0.3603 0.4746
4.000 1.0755 0.01001 0.00378 -0.1200 0.3552 0.4818
4.250 1.1008 0.01013 0.00391 -0.1194 0.3511 0.4880
4.500 1.1270 0.01021 0.00401 -0.1188 0.3475 0.4931
4.750 1.1522 0.01032 0.00412 -0.1181 0.3432 0.4984
5.000 1.1763 0.01046 0.00426 -0.1173 0.3385 0.5052
5.250 1.2001 0.01062 0.00442 -0.1163 0.3338 0.5118
5.500 1.2256 0.01072 0.00453 -0.1157 0.3303 0.5173
5.750 1.2498 0.01083 0.00467 -0.1149 0.3257 0.5248
6.000 1.2726 0.01100 0.00483 -0.1138 0.3205 0.5319
6.250 1.2951 0.01118 0.00499 -0.1127 0.3154 0.5381
6.500 1.3177 0.01128 0.00514 -0.1115 0.3101 0.5456
6.750 1.3378 0.01146 0.00530 -0.1099 0.3039 0.5530
7.000 1.3581 0.01166 0.00549 -0.1084 0.2980 0.5597
7.250 1.3794 0.01181 0.00567 -0.1071 0.2921 0.5674
7.500 1.3985 0.01206 0.00590 -0.1054 0.2861 0.5750
7.750 1.4183 0.01227 0.00612 -0.1039 0.2802 0.5827
8.000 1.4385 0.01248 0.00635 -0.1024 0.2745 0.5916
8.250 1.4557 0.01279 0.00664 -0.1005 0.2675 0.5998
8.500 1.4753 0.01301 0.00689 -0.0990 0.2617 0.6097
8.750 1.4930 0.01330 0.00718 -0.0972 0.2551 0.6206
9.000 1.5097 0.01361 0.00751 -0.0953 0.2487 0.6353
9.250 1.5270 0.01384 0.00784 -0.0935 0.2427 0.6674
9.500 1.5933 0.01403 0.00849 -0.1023 0.2320 1.0000
9.750 1.6118 0.01444 0.00887 -0.1009 0.2254 1.0000
10.000 1.6285 0.01493 0.00933 -0.0992 0.2190 1.0000
10.250 1.6476 0.01531 0.00972 -0.0980 0.2145 1.0000
10.500 1.6643 0.01582 0.01021 -0.0964 0.2087 1.0000
10.750 1.6802 0.01638 0.01075 -0.0949 0.2032 1.0000
11.000 1.6979 0.01686 0.01124 -0.0936 0.1988 1.0000
11.250 1.7125 0.01750 0.01186 -0.0919 0.1938 1.0000
11.500 1.7273 0.01815 0.01251 -0.0904 0.1892 1.0000
11.750 1.7437 0.01872 0.01311 -0.0891 0.1856 1.0000
12.000 1.7579 0.01943 0.01382 -0.0876 0.1817 1.0000
12.250 1.7695 0.02031 0.01470 -0.0859 0.1775 1.0000
12.500 1.7843 0.02104 0.01546 -0.0846 0.1745 1.0000
12.750 1.7983 0.02182 0.01627 -0.0833 0.1714 1.0000
13.000 1.8097 0.02279 0.01726 -0.0819 0.1679 1.0000
13.250 1.8188 0.02396 0.01843 -0.0803 0.1641 1.0000
13.500 1.8312 0.02494 0.01946 -0.0791 0.1615 1.0000
13.750 1.8430 0.02599 0.02054 -0.0780 0.1586 1.0000
14.000 1.8516 0.02730 0.02188 -0.0767 0.1550 1.0000
14.250 1.8569 0.02893 0.02352 -0.0753 0.1512 1.0000
14.500 1.8666 0.03025 0.02490 -0.0744 0.1483 1.0000
14.750 1.8735 0.03185 0.02652 -0.0733 0.1440 1.0000
15.000 1.8748 0.03399 0.02867 -0.0722 0.1393 1.0000
15.250 1.8803 0.03582 0.03055 -0.0713 0.1350 1.0000
15.500 1.8797 0.03826 0.03301 -0.0703 0.1291 1.0000
15.750 1.8780 0.04088 0.03565 -0.0695 0.1228 1.0000
16.000 1.8695 0.04427 0.03903 -0.0687 0.1148 1.0000
16.250 1.8563 0.04824 0.04300 -0.0680 0.1054 1.0000
16.500 1.8383 0.05288 0.04764 -0.0675 0.0964 1.0000
16.750 1.8185 0.05789 0.05267 -0.0672 0.0888 1.0000
17.000 1.8008 0.06276 0.05759 -0.0672 0.0832 1.0000
17.250 1.7833 0.06777 0.06265 -0.0674 0.0791 1.0000
17.500 1.7681 0.07258 0.06751 -0.0677 0.0761 1.0000
17.750 1.7509 0.07772 0.07271 -0.0681 0.0736 1.0000
18.000 1.7374 0.08248 0.07756 -0.0686 0.0717 1.0000
18.250 1.7251 0.08710 0.08226 -0.0692 0.0704 1.0000
18.500 1.7105 0.09207 0.08731 -0.0699 0.0689 1.0000
18.750 1.6955 0.09716 0.09246 -0.0708 0.0675 1.0000
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