GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 500,000 Max Cl/Cd: 80.3 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe766-il-500000.txt Download as CSV file: xf-goe766-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9431 0.07542 0.07222 -0.0316 1.0000 0.0292
-14.750 -0.9835 0.06479 0.06137 -0.0397 1.0000 0.0291
-14.500 -1.0143 0.05725 0.05361 -0.0448 1.0000 0.0291
-14.250 -1.0428 0.05134 0.04745 -0.0478 1.0000 0.0291
-14.000 -1.0632 0.04725 0.04313 -0.0485 1.0000 0.0292
-13.750 -1.0844 0.04360 0.03925 -0.0476 1.0000 0.0294
-13.500 -1.0978 0.04044 0.03591 -0.0457 1.0000 0.0296
-13.250 -1.0985 0.03858 0.03399 -0.0437 1.0000 0.0299
-13.000 -1.0975 0.03714 0.03248 -0.0413 1.0000 0.0301
-12.750 -1.0952 0.03595 0.03122 -0.0386 1.0000 0.0304
-12.500 -1.0904 0.03507 0.03028 -0.0357 1.0000 0.0308
-12.250 -1.0812 0.03413 0.02929 -0.0335 1.0000 0.0312
-12.000 -1.0723 0.03300 0.02805 -0.0313 1.0000 0.0317
-11.750 -1.0635 0.03175 0.02665 -0.0291 1.0000 0.0322
-11.500 -1.0543 0.03046 0.02517 -0.0267 1.0000 0.0329
-11.250 -1.0436 0.02920 0.02369 -0.0245 1.0000 0.0333
-11.000 -1.0312 0.02826 0.02254 -0.0222 1.0000 0.0337
-10.750 -1.0179 0.02617 0.02030 -0.0205 1.0000 0.0343
-10.500 -0.9998 0.02516 0.01928 -0.0192 1.0000 0.0349
-10.250 -0.9812 0.02452 0.01863 -0.0178 1.0000 0.0355
-10.000 -0.9626 0.02380 0.01784 -0.0163 1.0000 0.0361
-9.750 -0.9437 0.02306 0.01702 -0.0148 1.0000 0.0368
-9.500 -0.9247 0.02224 0.01611 -0.0133 1.0000 0.0375
-9.250 -0.9054 0.02144 0.01520 -0.0117 1.0000 0.0381
-9.000 -0.8856 0.02084 0.01448 -0.0102 1.0000 0.0386
-8.750 -0.8662 0.01978 0.01333 -0.0087 1.0000 0.0394
-8.500 -0.8463 0.01886 0.01243 -0.0074 1.0000 0.0402
-8.250 -0.8258 0.01826 0.01183 -0.0060 1.0000 0.0409
-8.000 -0.8053 0.01769 0.01123 -0.0045 1.0000 0.0416
-7.750 -0.7847 0.01715 0.01066 -0.0030 1.0000 0.0424
-7.500 -0.7643 0.01662 0.01009 -0.0015 1.0000 0.0432
-7.250 -0.7436 0.01620 0.00962 0.0000 1.0000 0.0441
-7.000 -0.7227 0.01586 0.00923 0.0015 1.0000 0.0447
-6.750 -0.7056 0.01490 0.00829 0.0035 1.0000 0.0459
-6.500 -0.6866 0.01441 0.00783 0.0053 1.0000 0.0469
-6.250 -0.6674 0.01401 0.00742 0.0071 1.0000 0.0479
-6.000 -0.6482 0.01364 0.00705 0.0089 1.0000 0.0491
-5.750 -0.6290 0.01330 0.00669 0.0107 1.0000 0.0502
-5.500 -0.5937 0.01287 0.00624 0.0092 0.9972 0.0518
-5.250 -0.5557 0.01228 0.00570 0.0069 0.9929 0.0544
-5.000 -0.5181 0.01188 0.00532 0.0050 0.9872 0.0569
-4.750 -0.4775 0.01144 0.00487 0.0025 0.9821 0.0600
-4.500 -0.4425 0.01097 0.00447 0.0011 0.9732 0.0643
-4.250 -0.4046 0.01054 0.00407 -0.0008 0.9631 0.0704
-4.000 -0.3635 0.01009 0.00368 -0.0033 0.9474 0.0810
-3.750 -0.3203 0.00957 0.00333 -0.0064 0.9220 0.1104
-3.500 -0.2864 0.00929 0.00310 -0.0073 0.8817 0.1434
-3.250 -0.2605 0.00916 0.00289 -0.0065 0.8251 0.1638
-3.000 -0.2385 0.00916 0.00269 -0.0049 0.7544 0.1822
-2.750 -0.2167 0.00915 0.00254 -0.0034 0.6974 0.2048
-2.500 -0.1947 0.00901 0.00239 -0.0021 0.6543 0.2447
-2.250 -0.1742 0.00864 0.00224 -0.0006 0.6197 0.3328
-2.000 -0.1530 0.00831 0.00212 0.0008 0.5900 0.4188
-1.750 -0.1330 0.00795 0.00203 0.0024 0.5653 0.5124
-1.500 -0.1122 0.00769 0.00200 0.0041 0.5440 0.5992
-1.250 -0.0895 0.00757 0.00199 0.0054 0.5255 0.6571
-1.000 -0.0663 0.00747 0.00199 0.0068 0.5099 0.7053
-0.750 -0.0425 0.00741 0.00200 0.0080 0.4958 0.7473
-0.500 -0.0179 0.00734 0.00203 0.0091 0.4830 0.7853
-0.250 0.0075 0.00733 0.00207 0.0100 0.4713 0.8177
0.000 0.0340 0.00737 0.00210 0.0107 0.4595 0.8414
0.250 0.0616 0.00739 0.00214 0.0112 0.4479 0.8639
0.500 0.0896 0.00745 0.00220 0.0116 0.4370 0.8878
0.750 0.1216 0.00757 0.00230 0.0112 0.4257 0.9103
1.000 0.1554 0.00768 0.00240 0.0103 0.4146 0.9263
1.250 0.1880 0.00783 0.00249 0.0097 0.4038 0.9383
1.500 0.2264 0.00801 0.00260 0.0077 0.3913 0.9458
1.750 0.2594 0.00816 0.00271 0.0070 0.3791 0.9555
2.000 0.3011 0.00835 0.00282 0.0043 0.3656 0.9593
2.250 0.3406 0.00857 0.00297 0.0022 0.3526 0.9657
2.500 0.3796 0.00878 0.00309 0.0001 0.3394 0.9713
2.750 0.4198 0.00894 0.00319 -0.0024 0.3265 0.9748
3.000 0.4563 0.00911 0.00331 -0.0040 0.3150 0.9801
3.250 0.4945 0.00929 0.00340 -0.0061 0.3032 0.9839
3.500 0.5339 0.00943 0.00349 -0.0085 0.2924 0.9870
3.750 0.5704 0.00957 0.00359 -0.0103 0.2838 0.9907
4.000 0.6059 0.00973 0.00369 -0.0119 0.2747 0.9939
4.250 0.6439 0.00981 0.00375 -0.0140 0.2654 0.9967
4.500 0.6808 0.00997 0.00384 -0.0160 0.2571 0.9995
4.750 0.7062 0.01004 0.00393 -0.0156 0.2515 1.0000
5.000 0.7280 0.01015 0.00403 -0.0144 0.2455 1.0000
5.250 0.7494 0.01033 0.00417 -0.0131 0.2397 1.0000
5.500 0.7719 0.01040 0.00429 -0.0120 0.2341 1.0000
5.750 0.7937 0.01056 0.00442 -0.0108 0.2278 1.0000
6.000 0.8157 0.01072 0.00458 -0.0096 0.2218 1.0000
6.250 0.8381 0.01085 0.00473 -0.0085 0.2152 1.0000
6.500 0.8597 0.01108 0.00492 -0.0073 0.2082 1.0000
6.750 0.8826 0.01119 0.00507 -0.0062 0.2008 1.0000
7.000 0.9044 0.01142 0.00527 -0.0050 0.1925 1.0000
7.250 0.9270 0.01159 0.00544 -0.0040 0.1830 1.0000
7.500 0.9491 0.01182 0.00566 -0.0029 0.1718 1.0000
7.750 0.9706 0.01211 0.00590 -0.0017 0.1572 1.0000
8.000 0.9908 0.01251 0.00621 -0.0003 0.1394 1.0000
8.250 1.0101 0.01301 0.00661 0.0011 0.1229 1.0000
8.500 1.0291 0.01354 0.00707 0.0026 0.1093 1.0000
8.750 1.0476 0.01410 0.00758 0.0042 0.0987 1.0000
9.000 1.0663 0.01463 0.00809 0.0057 0.0905 1.0000
9.250 1.0855 0.01512 0.00859 0.0072 0.0842 1.0000
9.500 1.1025 0.01577 0.00920 0.0089 0.0785 1.0000
9.750 1.1220 0.01621 0.00969 0.0103 0.0749 1.0000
10.000 1.1397 0.01678 0.01025 0.0119 0.0713 1.0000
10.250 1.1551 0.01749 0.01097 0.0138 0.0682 1.0000
10.500 1.1736 0.01796 0.01151 0.0153 0.0659 1.0000
10.750 1.1905 0.01852 0.01210 0.0169 0.0635 1.0000
11.000 1.2033 0.01931 0.01290 0.0191 0.0612 1.0000
11.250 1.2162 0.02006 0.01370 0.0212 0.0595 1.0000
11.500 1.2314 0.02064 0.01435 0.0230 0.0580 1.0000
11.750 1.2450 0.02126 0.01503 0.0250 0.0564 1.0000
12.000 1.2553 0.02199 0.01580 0.0273 0.0550 1.0000
12.250 1.2580 0.02289 0.01673 0.0308 0.0538 1.0000
12.500 1.2552 0.02419 0.01806 0.0344 0.0525 1.0000
12.750 1.2645 0.02502 0.01899 0.0363 0.0518 1.0000
13.000 1.2723 0.02602 0.02008 0.0380 0.0508 1.0000
13.250 1.2787 0.02722 0.02137 0.0395 0.0498 1.0000
13.500 1.2836 0.02869 0.02291 0.0405 0.0489 1.0000
13.750 1.2873 0.03045 0.02474 0.0411 0.0480 1.0000
14.000 1.2883 0.03270 0.02705 0.0412 0.0472 1.0000
14.250 1.2849 0.03561 0.03001 0.0408 0.0462 1.0000
14.500 1.2840 0.03845 0.03293 0.0402 0.0456 1.0000
14.750 1.2874 0.04105 0.03566 0.0392 0.0450 1.0000
15.000 1.2893 0.04389 0.03862 0.0381 0.0443 1.0000
15.250 1.2890 0.04699 0.04182 0.0369 0.0436 1.0000
15.500 1.2877 0.05027 0.04518 0.0355 0.0428 1.0000
15.750 1.2850 0.05361 0.04860 0.0343 0.0423 1.0000
16.000 1.2821 0.05704 0.05210 0.0329 0.0418 1.0000
16.250 1.2773 0.06067 0.05579 0.0315 0.0411 1.0000
16.500 1.2732 0.06406 0.05922 0.0304 0.0407 1.0000
16.750 1.2688 0.06715 0.06231 0.0300 0.0398 1.0000
17.000 1.2627 0.07142 0.06672 0.0278 0.0394 1.0000
17.250 1.2575 0.07541 0.07082 0.0261 0.0390 1.0000
17.500 1.2515 0.07970 0.07522 0.0240 0.0385 1.0000
17.750 1.2459 0.08394 0.07956 0.0221 0.0379 1.0000
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