GOE 13K AIRFOIL (goe13k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 13K AIRFOIL (goe13k-il) Reynolds number: 500,000 Max Cl/Cd: 92.87 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe13k-il-500000.txt Download as CSV file: xf-goe13k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 13K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0036 0.09301 0.08995 -0.1590 0.9308 0.0519
-10.750 0.0057 0.08930 0.08623 -0.1625 0.9304 0.0535
-10.250 -0.0372 0.07935 0.07631 -0.1641 0.9202 0.0562
-10.000 -0.0200 0.07731 0.07427 -0.1655 0.9197 0.0566
-9.750 -0.0034 0.07516 0.07211 -0.1673 0.9191 0.0572
-9.500 0.0094 0.07202 0.06896 -0.1704 0.9185 0.0579
-9.250 0.0205 0.06830 0.06522 -0.1746 0.9179 0.0599
-9.000 -0.1540 0.05036 0.04691 -0.1750 0.9009 0.0634
-8.750 -0.1805 0.04982 0.04637 -0.1660 0.8922 0.0635
-8.500 -0.1576 0.04856 0.04514 -0.1666 0.8914 0.0639
-8.250 -0.1334 0.04762 0.04420 -0.1674 0.8907 0.0644
-8.000 -0.1156 0.04561 0.04213 -0.1681 0.8897 0.0649
-7.750 -0.3275 0.03246 0.02754 -0.1298 0.8652 0.0559
-7.500 -0.3203 0.03117 0.02602 -0.1263 0.8623 0.0557
-7.250 -0.3078 0.02880 0.02352 -0.1245 0.8609 0.0564
-7.000 -0.2374 0.03317 0.02864 -0.1321 0.8618 0.0610
-6.750 -0.2683 0.02555 0.01988 -0.1225 0.8592 0.0568
-6.500 -0.2444 0.02419 0.01834 -0.1221 0.8585 0.0571
-6.250 -0.2779 0.02508 0.01921 -0.1096 0.8474 0.0571
-6.000 -0.2551 0.02433 0.01841 -0.1089 0.8461 0.0577
-5.750 -0.2320 0.02338 0.01732 -0.1081 0.8451 0.0580
-5.500 -0.2060 0.02262 0.01646 -0.1079 0.8444 0.0587
-5.250 -0.1794 0.02171 0.01542 -0.1078 0.8438 0.0592
-5.000 -0.1514 0.02084 0.01440 -0.1079 0.8432 0.0597
-4.750 -0.1896 0.02195 0.01548 -0.0945 0.8318 0.0594
-4.500 -0.1661 0.02132 0.01474 -0.0937 0.8305 0.0599
-4.250 -0.1399 0.02068 0.01399 -0.0933 0.8296 0.0604
-4.000 -0.1119 0.02009 0.01331 -0.0933 0.8289 0.0610
-3.750 -0.0825 0.01954 0.01268 -0.0936 0.8284 0.0616
-3.500 -0.0514 0.01906 0.01212 -0.0943 0.8279 0.0623
-3.250 -0.0873 0.02043 0.01347 -0.0816 0.8166 0.0624
-3.000 -0.0599 0.02000 0.01298 -0.0814 0.8154 0.0627
-2.750 -0.0272 0.01903 0.01197 -0.0824 0.8149 0.0635
-2.500 0.0045 0.01830 0.01125 -0.0832 0.8144 0.0644
-2.250 0.0370 0.01775 0.01071 -0.0841 0.8138 0.0651
-2.000 0.0678 0.01732 0.01028 -0.0847 0.8133 0.0662
-1.750 0.1027 0.01679 0.00975 -0.0861 0.8129 0.0670
-1.500 0.1332 0.01646 0.00942 -0.0866 0.8123 0.0684
-1.250 0.1121 0.01751 0.01046 -0.0769 0.8044 0.0685
-1.000 0.1558 0.01688 0.00983 -0.0800 0.8059 0.0704
-0.750 0.1984 0.01628 0.00922 -0.0829 0.8068 0.0715
-0.500 0.2430 0.01547 0.00845 -0.0863 0.8074 0.0738
-0.250 0.2883 0.01491 0.00792 -0.0900 0.8082 0.0765
0.000 0.3347 0.01446 0.00747 -0.0939 0.8089 0.0796
1.000 0.7044 0.01167 0.00766 -0.1538 0.8134 0.9421
1.250 0.7278 0.01185 0.00779 -0.1526 0.8120 0.9813
1.500 0.8184 0.01195 0.00788 -0.1667 0.8127 0.9949
1.750 0.8911 0.01174 0.00765 -0.1768 0.8126 1.0000
2.000 0.9305 0.01154 0.00742 -0.1795 0.8112 1.0000
2.250 0.9701 0.01141 0.00727 -0.1823 0.8100 1.0000
2.500 0.9122 0.01223 0.00814 -0.1638 0.8013 1.0000
2.750 0.9403 0.01210 0.00799 -0.1639 0.7988 1.0000
3.000 0.9772 0.01187 0.00774 -0.1659 0.7968 1.0000
3.250 1.0266 0.01146 0.00729 -0.1706 0.7946 1.0000
3.500 0.9964 0.01200 0.00787 -0.1580 0.7864 1.0000
3.750 1.0308 0.01160 0.00744 -0.1593 0.7811 1.0000
4.000 1.0380 0.01161 0.00744 -0.1547 0.7730 1.0000
4.250 1.0578 0.01139 0.00717 -0.1527 0.7634 1.0000
4.500 1.0505 0.01174 0.00754 -0.1452 0.7533 1.0000
4.750 1.0692 0.01169 0.00744 -0.1432 0.7433 1.0000
5.000 1.0720 0.01201 0.00778 -0.1379 0.7333 1.0000
5.250 1.0797 0.01228 0.00805 -0.1337 0.7226 1.0000
5.500 1.0930 0.01246 0.00820 -0.1307 0.7104 1.0000
5.750 1.1005 0.01280 0.00852 -0.1266 0.6954 1.0000
6.000 1.1026 0.01330 0.00898 -0.1214 0.6718 1.0000
6.250 1.0976 0.01402 0.00949 -0.1149 0.6190 1.0000
6.500 1.0474 0.01642 0.01129 -0.1001 0.5181 1.0000
6.750 1.0330 0.01799 0.01259 -0.0926 0.4769 1.0000
7.000 1.0360 0.01896 0.01344 -0.0885 0.4539 1.0000
7.250 1.0429 0.01979 0.01419 -0.0851 0.4367 1.0000
7.500 1.0531 0.02051 0.01485 -0.0823 0.4229 1.0000
7.750 1.0643 0.02121 0.01549 -0.0798 0.4090 1.0000
8.000 1.0776 0.02183 0.01609 -0.0776 0.3960 1.0000
8.250 1.0903 0.02248 0.01671 -0.0754 0.3824 1.0000
8.500 1.1027 0.02317 0.01736 -0.0731 0.3668 1.0000
8.750 1.1143 0.02391 0.01804 -0.0708 0.3481 1.0000
9.000 1.1247 0.02474 0.01879 -0.0683 0.3241 1.0000
9.250 1.1311 0.02578 0.01966 -0.0654 0.2890 1.0000
9.500 1.1324 0.02713 0.02074 -0.0618 0.2425 1.0000
9.750 1.1353 0.02843 0.02177 -0.0585 0.1995 1.0000
10.000 1.1407 0.02962 0.02272 -0.0556 0.1623 1.0000
10.250 1.1504 0.03059 0.02357 -0.0534 0.1427 1.0000
10.500 1.1608 0.03154 0.02443 -0.0513 0.1273 1.0000
10.750 1.1729 0.03239 0.02523 -0.0495 0.1164 1.0000
11.000 1.1857 0.03324 0.02605 -0.0477 0.1083 1.0000
11.250 1.1972 0.03416 0.02694 -0.0459 0.1018 1.0000
11.500 1.2098 0.03502 0.02782 -0.0442 0.0967 1.0000
11.750 1.2228 0.03587 0.02867 -0.0426 0.0924 1.0000
12.000 1.2326 0.03693 0.02970 -0.0407 0.0876 1.0000
12.250 1.2467 0.03773 0.03056 -0.0394 0.0848 1.0000
12.500 1.2590 0.03865 0.03150 -0.0378 0.0818 1.0000
12.750 1.2687 0.03978 0.03261 -0.0360 0.0786 1.0000
13.000 1.2798 0.04081 0.03368 -0.0344 0.0763 1.0000
13.250 1.2924 0.04174 0.03467 -0.0330 0.0740 1.0000
13.500 1.3038 0.04276 0.03572 -0.0316 0.0713 1.0000
13.750 1.3120 0.04404 0.03699 -0.0298 0.0688 1.0000
14.000 1.3215 0.04523 0.03824 -0.0283 0.0667 1.0000
14.250 1.3333 0.04627 0.03934 -0.0270 0.0645 1.0000
14.500 1.3438 0.04742 0.04051 -0.0256 0.0623 1.0000
14.750 1.3487 0.04903 0.04213 -0.0238 0.0600 1.0000
15.000 1.3575 0.05035 0.04352 -0.0224 0.0584 1.0000
15.250 1.3687 0.05148 0.04473 -0.0213 0.0563 1.0000
15.500 1.3764 0.05292 0.04620 -0.0199 0.0544 1.0000
15.750 1.3798 0.05475 0.04803 -0.0182 0.0525 1.0000
16.000 1.3869 0.05628 0.04965 -0.0169 0.0508 1.0000
16.250 1.3956 0.05770 0.05114 -0.0158 0.0488 1.0000
16.500 1.4030 0.05926 0.05274 -0.0147 0.0472 1.0000
16.750 1.4032 0.06151 0.05500 -0.0132 0.0457 1.0000
17.000 1.4094 0.06323 0.05682 -0.0121 0.0443 1.0000
17.250 1.4143 0.06510 0.05877 -0.0111 0.0429 1.0000
17.500 1.4200 0.06692 0.06064 -0.0102 0.0412 1.0000
17.750 1.4197 0.06938 0.06313 -0.0091 0.0401 1.0000
18.000 1.4196 0.07186 0.06569 -0.0081 0.0390 1.0000
18.250 1.4232 0.07403 0.06796 -0.0074 0.0377 1.0000
18.500 1.4252 0.07639 0.07040 -0.0067 0.0368 1.0000
18.750 1.4254 0.07900 0.07307 -0.0062 0.0357 1.0000
19.000 1.4222 0.08202 0.07613 -0.0057 0.0347 1.0000
19.250 1.4187 0.08513 0.07932 -0.0053 0.0340 1.0000
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