GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 200,000 Max Cl/Cd: 61.81 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe769-il-200000-n5.txt Download as CSV file: xf-goe769-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2350 0.11041 0.10671 -0.0207 1.0000 0.0481
-9.750 -0.2300 0.10747 0.10382 -0.0217 1.0000 0.0485
-9.250 -0.2451 0.09683 0.09321 -0.0274 1.0000 0.0410
-9.000 -0.2126 0.09332 0.08967 -0.0322 0.9278 0.0404
-8.750 -0.1734 0.08739 0.08354 -0.0428 0.8622 0.0392
-8.500 -0.1616 0.08237 0.07831 -0.0482 0.8153 0.0382
-8.250 -0.1856 0.07370 0.06952 -0.0537 0.7901 0.0368
-7.250 -0.3126 0.02927 0.02303 -0.0773 0.7317 0.0368
-7.000 -0.2949 0.02742 0.02086 -0.0766 0.7172 0.0370
-6.750 -0.2740 0.02619 0.01943 -0.0759 0.7040 0.0373
-6.500 -0.2523 0.02505 0.01805 -0.0751 0.6920 0.0376
-6.250 -0.2297 0.02395 0.01676 -0.0744 0.6801 0.0381
-6.000 -0.2067 0.02291 0.01547 -0.0737 0.6697 0.0385
-5.750 -0.1830 0.02190 0.01423 -0.0730 0.6584 0.0390
-5.500 -0.1588 0.02100 0.01308 -0.0723 0.6483 0.0397
-5.250 -0.1339 0.02014 0.01197 -0.0716 0.6377 0.0405
-5.000 -0.1086 0.01944 0.01107 -0.0709 0.6285 0.0414
-4.750 -0.0828 0.01895 0.01055 -0.0703 0.6180 0.0420
-4.500 -0.0569 0.01849 0.00999 -0.0697 0.6082 0.0428
-4.250 -0.0307 0.01797 0.00937 -0.0691 0.5972 0.0436
-4.000 -0.0046 0.01748 0.00874 -0.0684 0.5875 0.0446
-3.750 0.0219 0.01700 0.00813 -0.0678 0.5769 0.0456
-3.500 0.0481 0.01662 0.00771 -0.0671 0.5670 0.0466
-3.250 0.0747 0.01630 0.00735 -0.0666 0.5553 0.0478
-3.000 0.1013 0.01601 0.00698 -0.0660 0.5443 0.0496
-2.750 0.1277 0.01572 0.00662 -0.0653 0.5322 0.0516
-2.500 0.1543 0.01550 0.00636 -0.0647 0.5185 0.0539
-2.250 0.1807 0.01526 0.00604 -0.0641 0.5043 0.0567
-2.000 0.2069 0.01509 0.00580 -0.0634 0.4909 0.0597
-1.750 0.2336 0.01490 0.00558 -0.0629 0.4783 0.0637
-1.500 0.2603 0.01478 0.00541 -0.0623 0.4673 0.0694
-1.250 0.2869 0.01471 0.00528 -0.0617 0.4561 0.0764
-1.000 0.3137 0.01464 0.00519 -0.0612 0.4459 0.0840
-0.750 0.3402 0.01461 0.00512 -0.0606 0.4363 0.0919
-0.500 0.3671 0.01457 0.00507 -0.0601 0.4268 0.1005
-0.250 0.3935 0.01457 0.00503 -0.0595 0.4176 0.1096
0.000 0.4204 0.01455 0.00501 -0.0591 0.4090 0.1200
0.250 0.4468 0.01455 0.00498 -0.0585 0.4006 0.1311
0.500 0.4733 0.01454 0.00496 -0.0580 0.3927 0.1427
0.750 0.4997 0.01451 0.00496 -0.0574 0.3843 0.1553
1.000 0.5257 0.01451 0.00496 -0.0569 0.3769 0.1714
1.500 0.5775 0.01440 0.00505 -0.0557 0.3619 0.2475
1.750 0.6025 0.01423 0.00514 -0.0551 0.3547 0.3343
2.000 0.6207 0.01342 0.00527 -0.0532 0.3476 0.6343
2.500 0.7132 0.01324 0.00551 -0.0597 0.3296 1.0000
2.750 0.7375 0.01347 0.00561 -0.0588 0.3229 1.0000
3.000 0.7626 0.01366 0.00574 -0.0580 0.3154 1.0000
3.250 0.7870 0.01390 0.00586 -0.0572 0.3081 1.0000
3.500 0.8117 0.01412 0.00602 -0.0564 0.3013 1.0000
3.750 0.8364 0.01436 0.00618 -0.0556 0.2943 1.0000
4.000 0.8603 0.01464 0.00636 -0.0548 0.2879 1.0000
4.250 0.8852 0.01487 0.00655 -0.0540 0.2808 1.0000
4.500 0.9090 0.01515 0.00675 -0.0532 0.2741 1.0000
4.750 0.9332 0.01543 0.00698 -0.0524 0.2681 1.0000
5.000 0.9572 0.01571 0.00722 -0.0516 0.2620 1.0000
5.250 0.9803 0.01605 0.00746 -0.0507 0.2565 1.0000
5.500 1.0043 0.01634 0.00774 -0.0499 0.2511 1.0000
5.750 1.0276 0.01666 0.00802 -0.0491 0.2457 1.0000
6.000 1.0499 0.01704 0.00832 -0.0481 0.2412 1.0000
6.250 1.0731 0.01738 0.00865 -0.0473 0.2369 1.0000
6.500 1.0959 0.01773 0.00899 -0.0464 0.2325 1.0000
6.750 1.1178 0.01813 0.00934 -0.0454 0.2283 1.0000
7.000 1.1386 0.01858 0.00972 -0.0443 0.2247 1.0000
7.250 1.1611 0.01894 0.01011 -0.0435 0.2211 1.0000
7.500 1.1827 0.01934 0.01052 -0.0425 0.2177 1.0000
7.750 1.2033 0.01978 0.01095 -0.0414 0.2144 1.0000
8.000 1.2227 0.02027 0.01139 -0.0402 0.2113 1.0000
8.250 1.2423 0.02076 0.01187 -0.0390 0.2084 1.0000
8.500 1.2624 0.02119 0.01235 -0.0379 0.2053 1.0000
8.750 1.2815 0.02166 0.01286 -0.0366 0.2024 1.0000
9.000 1.2993 0.02217 0.01337 -0.0353 0.1998 1.0000
9.250 1.3153 0.02273 0.01391 -0.0337 0.1974 1.0000
9.500 1.3292 0.02336 0.01450 -0.0318 0.1951 1.0000
9.750 1.3447 0.02389 0.01510 -0.0301 0.1927 1.0000
10.000 1.3592 0.02446 0.01574 -0.0284 0.1902 1.0000
10.250 1.3728 0.02510 0.01642 -0.0268 0.1877 1.0000
10.500 1.3856 0.02580 0.01716 -0.0251 0.1855 1.0000
10.750 1.3977 0.02658 0.01795 -0.0235 0.1835 1.0000
11.000 1.4094 0.02745 0.01880 -0.0220 0.1816 1.0000
11.250 1.4216 0.02833 0.01973 -0.0207 0.1798 1.0000
11.500 1.4332 0.02924 0.02075 -0.0195 0.1777 1.0000
11.750 1.4439 0.03026 0.02184 -0.0183 0.1755 1.0000
12.000 1.4539 0.03135 0.02300 -0.0173 0.1734 1.0000
12.250 1.4632 0.03254 0.02424 -0.0163 0.1715 1.0000
12.500 1.4720 0.03382 0.02554 -0.0154 0.1697 1.0000
12.750 1.4814 0.03512 0.02684 -0.0146 0.1681 1.0000
13.000 1.4903 0.03652 0.02831 -0.0139 0.1666 1.0000
13.250 1.4975 0.03809 0.03001 -0.0133 0.1649 1.0000
13.500 1.5039 0.03977 0.03180 -0.0129 0.1630 1.0000
13.750 1.5097 0.04154 0.03366 -0.0125 0.1612 1.0000
14.000 1.5151 0.04339 0.03558 -0.0122 0.1595 1.0000
14.250 1.5201 0.04529 0.03753 -0.0120 0.1579 1.0000
14.500 1.5255 0.04717 0.03943 -0.0118 0.1563 1.0000
14.750 1.5329 0.04888 0.04114 -0.0115 0.1549 1.0000
15.000 1.5332 0.05143 0.04385 -0.0117 0.1535 1.0000
15.250 1.5331 0.05408 0.04665 -0.0119 0.1520 1.0000
15.500 1.5326 0.05684 0.04953 -0.0123 0.1504 1.0000
15.750 1.5318 0.05967 0.05248 -0.0127 0.1489 1.0000
16.000 1.5308 0.06262 0.05552 -0.0133 0.1474 1.0000
16.250 1.5303 0.06556 0.05854 -0.0140 0.1460 1.0000
16.500 1.5331 0.06809 0.06110 -0.0145 0.1446 1.0000
16.750 1.5404 0.07002 0.06302 -0.0147 0.1433 1.0000
17.000 1.5304 0.07447 0.06765 -0.0162 0.1419 1.0000
17.250 1.5154 0.07981 0.07319 -0.0183 0.1404 1.0000
17.500 1.5002 0.08531 0.07888 -0.0205 0.1388 1.0000
17.750 1.4855 0.09090 0.08462 -0.0228 0.1372 1.0000
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