GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 592 AIRFOIL (goe592-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.45 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe592-il-1000000.txt Download as CSV file: xf-goe592-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 592 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4314 0.02791 0.02492 -0.1751 0.8717 0.0303
-12.250 -0.4298 0.02543 0.02224 -0.1744 0.8648 0.0305
-12.000 -0.4179 0.02399 0.02064 -0.1737 0.8590 0.0308
-11.750 -0.4048 0.02261 0.01910 -0.1728 0.8534 0.0312
-11.500 -0.3904 0.02130 0.01762 -0.1719 0.8476 0.0315
-11.250 -0.3737 0.02016 0.01630 -0.1710 0.8422 0.0318
-11.000 -0.3550 0.01920 0.01516 -0.1702 0.8372 0.0321
-10.750 -0.3345 0.01839 0.01423 -0.1695 0.8321 0.0324
-10.500 -0.3127 0.01773 0.01342 -0.1688 0.8267 0.0326
-10.250 -0.2966 0.01631 0.01177 -0.1677 0.8210 0.0331
-10.000 -0.2743 0.01563 0.01104 -0.1670 0.8160 0.0335
-9.750 -0.2502 0.01519 0.01054 -0.1665 0.8106 0.0339
-9.500 -0.2251 0.01489 0.01017 -0.1660 0.8054 0.0344
-9.250 -0.2001 0.01450 0.00973 -0.1656 0.8004 0.0349
-9.000 -0.1752 0.01409 0.00923 -0.1651 0.7947 0.0354
-8.750 -0.1506 0.01367 0.00869 -0.1645 0.7889 0.0359
-8.500 -0.1253 0.01328 0.00819 -0.1641 0.7837 0.0363
-8.250 -0.0997 0.01292 0.00775 -0.1636 0.7780 0.0366
-8.000 -0.0755 0.01239 0.00709 -0.1630 0.7722 0.0372
-7.750 -0.0507 0.01194 0.00659 -0.1625 0.7666 0.0378
-7.500 -0.0245 0.01166 0.00628 -0.1621 0.7606 0.0384
-7.250 0.0017 0.01146 0.00602 -0.1617 0.7546 0.0391
-7.000 0.0283 0.01128 0.00579 -0.1613 0.7490 0.0398
-6.750 0.0549 0.01106 0.00551 -0.1610 0.7429 0.0406
-6.500 0.0812 0.01089 0.00524 -0.1605 0.7368 0.0412
-6.250 0.1068 0.01052 0.00482 -0.1600 0.7312 0.0421
-6.000 0.1332 0.01030 0.00458 -0.1597 0.7251 0.0430
-5.750 0.1595 0.01019 0.00441 -0.1592 0.7189 0.0439
-5.500 0.1865 0.01005 0.00425 -0.1589 0.7133 0.0449
-5.250 0.2134 0.00993 0.00407 -0.1586 0.7072 0.0460
-5.000 0.2391 0.00973 0.00380 -0.1580 0.7012 0.0472
-4.750 0.2660 0.00962 0.00369 -0.1578 0.6959 0.0485
-4.500 0.2932 0.00956 0.00362 -0.1575 0.6901 0.0500
-4.250 0.3197 0.00952 0.00351 -0.1570 0.6843 0.0514
-4.000 0.3461 0.00935 0.00333 -0.1567 0.6792 0.0530
-3.750 0.3732 0.00930 0.00328 -0.1564 0.6738 0.0546
-3.500 0.3999 0.00928 0.00323 -0.1560 0.6684 0.0563
-3.250 0.4266 0.00929 0.00318 -0.1556 0.6633 0.0577
-3.000 0.4532 0.00912 0.00303 -0.1553 0.6585 0.0598
-2.750 0.4800 0.00913 0.00303 -0.1550 0.6535 0.0616
-2.500 0.5062 0.00915 0.00300 -0.1545 0.6484 0.0635
-2.250 0.5334 0.00916 0.00299 -0.1543 0.6441 0.0647
-2.000 0.5593 0.00897 0.00282 -0.1538 0.6394 0.0671
-1.750 0.5856 0.00897 0.00281 -0.1534 0.6347 0.0689
-1.500 0.6113 0.00900 0.00280 -0.1529 0.6297 0.0708
-1.250 0.6384 0.00899 0.00279 -0.1526 0.6258 0.0723
-1.000 0.6641 0.00884 0.00265 -0.1522 0.6213 0.0747
-0.750 0.6897 0.00882 0.00263 -0.1516 0.6168 0.0768
-0.500 0.7149 0.00886 0.00263 -0.1510 0.6119 0.0789
-0.250 0.7415 0.00883 0.00261 -0.1507 0.6082 0.0808
0.000 0.7671 0.00877 0.00255 -0.1502 0.6038 0.0829
0.250 0.7920 0.00874 0.00252 -0.1496 0.5993 0.0858
0.500 0.8163 0.00879 0.00253 -0.1488 0.5943 0.0882
0.750 0.8423 0.00876 0.00253 -0.1484 0.5906 0.0905
1.000 0.8676 0.00874 0.00252 -0.1478 0.5862 0.0931
1.250 0.8916 0.00875 0.00253 -0.1470 0.5815 0.0976
1.500 0.9150 0.00881 0.00257 -0.1461 0.5765 0.1015
1.750 0.9400 0.00878 0.00259 -0.1455 0.5724 0.1086
2.000 0.9638 0.00877 0.00264 -0.1447 0.5676 0.1255
2.250 0.9851 0.00876 0.00271 -0.1434 0.5624 0.1704
2.500 1.0055 0.00869 0.00282 -0.1420 0.5576 0.2490
2.750 1.0203 0.00814 0.00302 -0.1396 0.5523 0.5803
3.000 1.0862 0.00768 0.00339 -0.1482 0.5442 1.0000
3.250 1.1055 0.00778 0.00346 -0.1464 0.5385 1.0000
3.500 1.1239 0.00789 0.00354 -0.1445 0.5317 1.0000
4.000 1.1607 0.00818 0.00376 -0.1407 0.5179 1.0000
4.250 1.1789 0.00836 0.00390 -0.1389 0.5112 1.0000
4.500 1.1986 0.00852 0.00404 -0.1374 0.5055 1.0000
4.750 1.2193 0.00868 0.00418 -0.1360 0.4989 1.0000
5.000 1.2370 0.00891 0.00436 -0.1342 0.4920 1.0000
5.250 1.2572 0.00909 0.00453 -0.1329 0.4838 1.0000
5.500 1.2745 0.00937 0.00475 -0.1310 0.4757 1.0000
5.750 1.2950 0.00957 0.00495 -0.1298 0.4686 1.0000
6.000 1.3136 0.00984 0.00519 -0.1282 0.4611 1.0000
6.250 1.3323 0.01011 0.00544 -0.1268 0.4541 1.0000
6.500 1.3520 0.01038 0.00569 -0.1255 0.4466 1.0000
6.750 1.3687 0.01074 0.00601 -0.1237 0.4381 1.0000
7.000 1.3876 0.01105 0.00630 -0.1224 0.4293 1.0000
7.250 1.4046 0.01144 0.00665 -0.1208 0.4205 1.0000
7.500 1.4222 0.01182 0.00702 -0.1193 0.4115 1.0000
7.750 1.4392 0.01224 0.00741 -0.1178 0.4028 1.0000
8.000 1.4553 0.01271 0.00784 -0.1162 0.3925 1.0000
8.250 1.4723 0.01316 0.00828 -0.1147 0.3832 1.0000
8.500 1.4865 0.01375 0.00882 -0.1129 0.3724 1.0000
8.750 1.5009 0.01436 0.00939 -0.1112 0.3596 1.0000
9.000 1.5157 0.01497 0.00997 -0.1096 0.3476 1.0000
9.250 1.5284 0.01570 0.01065 -0.1078 0.3355 1.0000
9.500 1.5402 0.01651 0.01140 -0.1059 0.3229 1.0000
9.750 1.5524 0.01732 0.01217 -0.1041 0.3100 1.0000
10.000 1.5640 0.01818 0.01300 -0.1023 0.2970 1.0000
10.250 1.5726 0.01924 0.01399 -0.1003 0.2823 1.0000
10.500 1.5816 0.02031 0.01501 -0.0983 0.2686 1.0000
10.750 1.5887 0.02154 0.01618 -0.0962 0.2545 1.0000
11.000 1.5955 0.02281 0.01739 -0.0942 0.2408 1.0000
11.250 1.6011 0.02421 0.01874 -0.0921 0.2270 1.0000
11.500 1.6059 0.02572 0.02019 -0.0901 0.2134 1.0000
11.750 1.6091 0.02737 0.02178 -0.0880 0.1980 1.0000
12.000 1.6113 0.02915 0.02348 -0.0859 0.1812 1.0000
12.250 1.6065 0.03152 0.02573 -0.0834 0.1578 1.0000
12.500 1.5988 0.03420 0.02828 -0.0808 0.1348 1.0000
12.750 1.5904 0.03704 0.03101 -0.0783 0.1161 1.0000
13.000 1.5907 0.03926 0.03320 -0.0767 0.1071 1.0000
13.250 1.5948 0.04119 0.03513 -0.0754 0.1015 1.0000
13.500 1.5979 0.04323 0.03718 -0.0741 0.0973 1.0000
13.750 1.6008 0.04534 0.03931 -0.0729 0.0936 1.0000
14.000 1.6084 0.04704 0.04106 -0.0720 0.0918 1.0000
14.250 1.6140 0.04897 0.04303 -0.0711 0.0900 1.0000
14.500 1.6180 0.05103 0.04511 -0.0701 0.0877 1.0000
14.750 1.6207 0.05326 0.04739 -0.0691 0.0860 1.0000
15.000 1.6202 0.05584 0.05000 -0.0681 0.0832 1.0000
15.250 1.6269 0.05772 0.05194 -0.0674 0.0822 1.0000
15.500 1.6337 0.05959 0.05387 -0.0668 0.0810 1.0000
15.750 1.6376 0.06180 0.05613 -0.0661 0.0798 1.0000
16.000 1.6410 0.06402 0.05840 -0.0654 0.0786 1.0000
16.250 1.6424 0.06652 0.06094 -0.0648 0.0773 1.0000
16.500 1.6428 0.06913 0.06360 -0.0641 0.0760 1.0000
16.750 1.6393 0.07220 0.06671 -0.0635 0.0743 1.0000
17.000 1.6381 0.07506 0.06964 -0.0629 0.0734 1.0000
17.250 1.6441 0.07708 0.07172 -0.0626 0.0727 1.0000
17.500 1.6486 0.07926 0.07397 -0.0622 0.0719 1.0000
17.750 1.6507 0.08176 0.07654 -0.0619 0.0710 1.0000
18.000 1.6539 0.08412 0.07894 -0.0616 0.0698 1.0000
18.250 1.6534 0.08695 0.08183 -0.0614 0.0687 1.0000
18.500 1.6535 0.08970 0.08463 -0.0612 0.0677 1.0000
18.750 1.6495 0.09299 0.08796 -0.0611 0.0665 1.0000
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