GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 200,000 Max Cl/Cd: 57.57 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe648-il-200000-n5.txt Download as CSV file: xf-goe648-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 648 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7041 0.05715 0.05243 -0.0812 1.0000 0.0319
-13.250 -0.7419 0.04974 0.04479 -0.0857 1.0000 0.0318
-13.000 -0.7678 0.04522 0.04010 -0.0871 1.0000 0.0320
-12.750 -0.7924 0.04201 0.03675 -0.0862 1.0000 0.0321
-12.500 -0.8174 0.03992 0.03454 -0.0830 1.0000 0.0323
-12.250 -0.8447 0.03863 0.03315 -0.0772 1.0000 0.0324
-12.000 -0.8474 0.03655 0.03082 -0.0758 0.9971 0.0331
-11.750 -0.8297 0.03420 0.02817 -0.0775 0.9917 0.0340
-11.500 -0.8061 0.03306 0.02702 -0.0785 0.9868 0.0346
-11.250 -0.7795 0.03196 0.02585 -0.0800 0.9827 0.0356
-11.000 -0.7578 0.03064 0.02436 -0.0805 0.9771 0.0366
-10.750 -0.7337 0.02915 0.02259 -0.0813 0.9719 0.0379
-10.500 -0.7053 0.02797 0.02132 -0.0826 0.9678 0.0389
-10.250 -0.6814 0.02717 0.02049 -0.0827 0.9608 0.0399
-10.000 -0.6513 0.02624 0.01945 -0.0839 0.9568 0.0412
-9.750 -0.6265 0.02525 0.01827 -0.0839 0.9510 0.0427
-9.500 -0.6007 0.02433 0.01725 -0.0841 0.9452 0.0439
-9.250 -0.5694 0.02361 0.01651 -0.0852 0.9417 0.0451
-9.000 -0.5424 0.02292 0.01575 -0.0854 0.9365 0.0466
-8.750 -0.5167 0.02217 0.01484 -0.0852 0.9302 0.0484
-8.500 -0.4851 0.02144 0.01407 -0.0862 0.9265 0.0499
-8.250 -0.4501 0.02081 0.01341 -0.0878 0.9238 0.0516
-8.000 -0.4289 0.02030 0.01283 -0.0866 0.9151 0.0535
-7.750 -0.3973 0.01964 0.01209 -0.0874 0.9105 0.0556
-7.500 -0.3629 0.01908 0.01152 -0.0888 0.9072 0.0577
-7.250 -0.3399 0.01863 0.01101 -0.0878 0.8985 0.0599
-7.000 -0.3084 0.01807 0.01039 -0.0885 0.8931 0.0627
-6.750 -0.2759 0.01759 0.00990 -0.0894 0.8880 0.0656
-6.500 -0.2497 0.01719 0.00942 -0.0889 0.8787 0.0688
-6.250 -0.2146 0.01661 0.00881 -0.0903 0.8723 0.0721
-6.000 -0.1895 0.01625 0.00842 -0.0896 0.8611 0.0757
-5.750 -0.1573 0.01580 0.00790 -0.0902 0.8523 0.0800
-5.500 -0.1309 0.01543 0.00751 -0.0898 0.8412 0.0839
-5.250 -0.1022 0.01511 0.00711 -0.0898 0.8311 0.0883
-5.000 -0.0748 0.01473 0.00672 -0.0895 0.8202 0.0930
-4.750 -0.0489 0.01447 0.00641 -0.0889 0.8088 0.0982
-4.500 -0.0212 0.01417 0.00608 -0.0887 0.7977 0.1039
-4.250 0.0038 0.01394 0.00581 -0.0879 0.7844 0.1108
-4.000 0.0286 0.01369 0.00556 -0.0871 0.7703 0.1189
-3.750 0.0539 0.01347 0.00532 -0.0863 0.7558 0.1293
-3.500 0.0790 0.01325 0.00508 -0.0855 0.7414 0.1436
-3.250 0.1035 0.01302 0.00489 -0.0847 0.7276 0.1627
-3.000 0.1276 0.01281 0.00471 -0.0837 0.7131 0.1881
-2.750 0.1516 0.01260 0.00457 -0.0828 0.6980 0.2185
-2.500 0.1757 0.01243 0.00443 -0.0819 0.6822 0.2508
-2.250 0.1996 0.01229 0.00431 -0.0809 0.6663 0.2837
-2.000 0.2234 0.01217 0.00421 -0.0799 0.6510 0.3161
-1.750 0.2468 0.01206 0.00413 -0.0788 0.6361 0.3503
-1.500 0.2695 0.01194 0.00408 -0.0776 0.6210 0.3926
-1.250 0.2918 0.01183 0.00407 -0.0763 0.6055 0.4422
-1.000 0.3141 0.01177 0.00408 -0.0749 0.5897 0.4905
-0.750 0.3362 0.01174 0.00411 -0.0735 0.5736 0.5363
-0.500 0.3582 0.01173 0.00414 -0.0721 0.5574 0.5783
-0.250 0.3798 0.01172 0.00417 -0.0705 0.5413 0.6172
0.000 0.4009 0.01172 0.00423 -0.0688 0.5247 0.6572
0.250 0.4216 0.01174 0.00431 -0.0670 0.5070 0.6997
0.500 0.4423 0.01179 0.00439 -0.0652 0.4877 0.7407
0.750 0.4633 0.01186 0.00446 -0.0635 0.4667 0.7821
1.000 0.4858 0.01197 0.00454 -0.0621 0.4444 0.8188
1.250 0.5140 0.01213 0.00465 -0.0620 0.4225 0.8561
1.500 0.5541 0.01239 0.00483 -0.0644 0.4014 0.8961
1.750 0.6044 0.01273 0.00503 -0.0691 0.3821 0.9339
2.250 0.6912 0.01342 0.00545 -0.0758 0.3564 1.0000
2.750 0.7277 0.01388 0.00572 -0.0721 0.3424 1.0000
3.000 0.7465 0.01412 0.00587 -0.0704 0.3360 1.0000
3.250 0.7651 0.01441 0.00605 -0.0686 0.3305 1.0000
3.500 0.7859 0.01461 0.00623 -0.0672 0.3253 1.0000
3.750 0.8061 0.01485 0.00641 -0.0657 0.3201 1.0000
4.000 0.8257 0.01514 0.00662 -0.0642 0.3154 1.0000
4.250 0.8461 0.01542 0.00684 -0.0628 0.3113 1.0000
4.500 0.8676 0.01564 0.00706 -0.0615 0.3069 1.0000
4.750 0.8884 0.01590 0.00729 -0.0602 0.3027 1.0000
5.000 0.9086 0.01620 0.00754 -0.0588 0.2985 1.0000
5.250 0.9286 0.01655 0.00781 -0.0574 0.2946 1.0000
5.500 0.9501 0.01678 0.00807 -0.0563 0.2910 1.0000
5.750 0.9706 0.01703 0.00834 -0.0549 0.2872 1.0000
6.000 0.9899 0.01731 0.00861 -0.0534 0.2832 1.0000
6.250 1.0087 0.01764 0.00889 -0.0518 0.2795 1.0000
6.500 1.0280 0.01799 0.00920 -0.0503 0.2760 1.0000
6.750 1.0478 0.01825 0.00952 -0.0489 0.2724 1.0000
7.000 1.0673 0.01854 0.00984 -0.0475 0.2687 1.0000
7.250 1.0859 0.01887 0.01017 -0.0460 0.2650 1.0000
7.500 1.1037 0.01924 0.01051 -0.0444 0.2614 1.0000
7.750 1.1225 0.01960 0.01089 -0.0430 0.2579 1.0000
8.000 1.1415 0.01993 0.01128 -0.0416 0.2540 1.0000
8.250 1.1596 0.02029 0.01168 -0.0402 0.2502 1.0000
8.500 1.1770 0.02069 0.01209 -0.0386 0.2467 1.0000
8.750 1.1939 0.02114 0.01251 -0.0371 0.2436 1.0000
9.000 1.2121 0.02155 0.01300 -0.0358 0.2401 1.0000
9.250 1.2294 0.02196 0.01349 -0.0343 0.2361 1.0000
9.500 1.2453 0.02243 0.01398 -0.0328 0.2322 1.0000
9.750 1.2594 0.02295 0.01448 -0.0310 0.2283 1.0000
10.000 1.2754 0.02346 0.01506 -0.0296 0.2242 1.0000
10.250 1.2908 0.02399 0.01566 -0.0281 0.2198 1.0000
10.500 1.3046 0.02458 0.01628 -0.0266 0.2158 1.0000
10.750 1.3171 0.02526 0.01695 -0.0249 0.2124 1.0000
11.000 1.3321 0.02589 0.01768 -0.0236 0.2083 1.0000
11.250 1.3458 0.02658 0.01844 -0.0222 0.2042 1.0000
11.500 1.3574 0.02737 0.01926 -0.0207 0.2003 1.0000
11.750 1.3677 0.02825 0.02015 -0.0191 0.1968 1.0000
12.000 1.3812 0.02906 0.02107 -0.0179 0.1929 1.0000
12.250 1.3923 0.02998 0.02206 -0.0166 0.1890 1.0000
12.500 1.4021 0.03101 0.02313 -0.0153 0.1857 1.0000
12.750 1.4104 0.03217 0.02430 -0.0140 0.1826 1.0000
13.000 1.4216 0.03322 0.02547 -0.0129 0.1791 1.0000
13.250 1.4306 0.03442 0.02676 -0.0118 0.1755 1.0000
13.500 1.4374 0.03580 0.02818 -0.0107 0.1720 1.0000
13.750 1.4421 0.03736 0.02975 -0.0096 0.1688 1.0000
14.000 1.4505 0.03877 0.03130 -0.0088 0.1652 1.0000
14.250 1.4565 0.04037 0.03300 -0.0080 0.1617 1.0000
14.500 1.4605 0.04219 0.03488 -0.0073 0.1586 1.0000
14.750 1.4626 0.04422 0.03693 -0.0067 0.1558 1.0000
15.000 1.4676 0.04611 0.03897 -0.0062 0.1529 1.0000
15.250 1.4711 0.04821 0.04119 -0.0059 0.1496 1.0000
15.500 1.4723 0.05058 0.04365 -0.0056 0.1465 1.0000
15.750 1.4711 0.05325 0.04637 -0.0055 0.1436 1.0000
16.000 1.4706 0.05596 0.04917 -0.0056 0.1408 1.0000
16.250 1.4698 0.05883 0.05220 -0.0058 0.1373 1.0000
16.500 1.4663 0.06206 0.05554 -0.0062 0.1340 1.0000
16.750 1.4596 0.06572 0.05926 -0.0068 0.1308 1.0000
17.000 1.4538 0.06943 0.06309 -0.0076 0.1276 1.0000
17.250 1.4459 0.07354 0.06734 -0.0086 0.1239 1.0000
17.500 1.4343 0.07822 0.07212 -0.0100 0.1203 1.0000
17.750 1.4211 0.08320 0.07716 -0.0115 0.1171 1.0000
18.000 1.4081 0.08839 0.08251 -0.0133 0.1133 1.0000
18.250 1.3922 0.09406 0.08829 -0.0154 0.1096 1.0000
18.500 1.3739 0.10018 0.09447 -0.0178 0.1061 1.0000
18.750 1.3563 0.10639 0.10083 -0.0203 0.1023 1.0000
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Polar data table (+)
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