GOE 775 AIRFOIL (goe775-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 775 AIRFOIL (goe775-il) Reynolds number: 100,000 Max Cl/Cd: 35.78 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe775-il-100000-n5.txt Download as CSV file: xf-goe775-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 775 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9509 0.10686 0.09916 -0.0386 1.0000 0.1002
-17.750 -0.9552 0.10280 0.09506 -0.0403 1.0000 0.1021
-17.500 -0.9508 0.10021 0.09248 -0.0413 1.0000 0.1041
-17.250 -0.9693 0.09398 0.08610 -0.0440 1.0000 0.1065
-17.000 -0.9958 0.08672 0.07859 -0.0472 1.0000 0.1089
-16.750 -1.0048 0.08229 0.07404 -0.0488 1.0000 0.1110
-16.500 -0.9998 0.07998 0.07176 -0.0493 1.0000 0.1133
-16.250 -1.0044 0.07632 0.06802 -0.0504 1.0000 0.1157
-16.000 -1.0147 0.07194 0.06346 -0.0517 1.0000 0.1184
-15.750 -1.0200 0.06836 0.05976 -0.0526 1.0000 0.1209
-15.500 -1.0152 0.06620 0.05764 -0.0528 1.0000 0.1233
-15.250 -1.0163 0.06333 0.05470 -0.0533 1.0000 0.1261
-15.000 -1.0205 0.06011 0.05134 -0.0538 1.0000 0.1291
-14.750 -1.0198 0.05757 0.04873 -0.0539 1.0000 0.1319
-14.500 -1.0162 0.05549 0.04666 -0.0538 1.0000 0.1347
-14.250 -1.0154 0.05311 0.04421 -0.0537 1.0000 0.1379
-14.000 -1.0161 0.05062 0.04157 -0.0535 1.0000 0.1414
-13.750 -1.0113 0.04881 0.03980 -0.0531 1.0000 0.1445
-13.500 -1.0079 0.04693 0.03790 -0.0525 1.0000 0.1478
-13.250 -1.0053 0.04499 0.03586 -0.0519 1.0000 0.1517
-13.000 -1.0013 0.04325 0.03407 -0.0511 1.0000 0.1554
-12.750 -0.9965 0.04171 0.03255 -0.0501 1.0000 0.1590
-12.500 -0.9924 0.04015 0.03094 -0.0490 1.0000 0.1633
-12.250 -0.9878 0.03869 0.02939 -0.0477 1.0000 0.1677
-12.000 -0.9826 0.03743 0.02817 -0.0462 1.0000 0.1716
-11.750 -0.9781 0.03619 0.02689 -0.0444 1.0000 0.1763
-11.500 -0.9734 0.03503 0.02566 -0.0425 1.0000 0.1814
-11.250 -0.9693 0.03401 0.02471 -0.0403 1.0000 0.1857
-11.000 -0.9661 0.03305 0.02372 -0.0377 1.0000 0.1909
-10.750 -0.9632 0.03218 0.02278 -0.0349 1.0000 0.1962
-10.500 -0.9622 0.03140 0.02208 -0.0316 1.0000 0.2008
-10.250 -0.9620 0.03071 0.02136 -0.0280 1.0000 0.2062
-10.000 -0.9623 0.03008 0.02069 -0.0241 1.0000 0.2116
-9.750 -0.9656 0.02953 0.02021 -0.0196 1.0000 0.2162
-9.500 -0.9702 0.02906 0.01974 -0.0147 1.0000 0.2214
-9.250 -0.9754 0.02867 0.01926 -0.0095 1.0000 0.2268
-9.000 -0.9816 0.02827 0.01895 -0.0041 1.0000 0.2313
-8.750 -0.9830 0.02787 0.01856 0.0005 1.0000 0.2370
-8.500 -0.9812 0.02749 0.01810 0.0046 1.0000 0.2435
-8.250 -0.9622 0.02696 0.01767 0.0053 0.9965 0.2510
-8.000 -0.9296 0.02646 0.01708 0.0036 0.9910 0.2615
-7.750 -0.9003 0.02592 0.01663 0.0025 0.9840 0.2705
-7.500 -0.8657 0.02545 0.01611 0.0005 0.9783 0.2811
-7.250 -0.8375 0.02497 0.01570 -0.0002 0.9702 0.2908
-7.000 -0.8026 0.02452 0.01525 -0.0021 0.9642 0.3015
-6.750 -0.7739 0.02411 0.01484 -0.0027 0.9557 0.3119
-6.500 -0.7396 0.02368 0.01446 -0.0044 0.9491 0.3227
-6.250 -0.7084 0.02330 0.01404 -0.0054 0.9411 0.3343
-6.000 -0.6757 0.02291 0.01373 -0.0066 0.9333 0.3451
-5.750 -0.6386 0.02250 0.01331 -0.0086 0.9275 0.3577
-5.500 -0.6141 0.02217 0.01303 -0.0080 0.9160 0.3691
-5.250 -0.5780 0.02177 0.01267 -0.0097 0.9097 0.3822
-4.750 -0.5209 0.02111 0.01207 -0.0098 0.8898 0.4074
-4.500 -0.4983 0.02085 0.01181 -0.0088 0.8766 0.4187
-4.250 -0.4653 0.02049 0.01148 -0.0096 0.8686 0.4310
-4.000 -0.4431 0.02026 0.01128 -0.0083 0.8546 0.4414
-3.750 -0.4131 0.01995 0.01097 -0.0085 0.8449 0.4537
-3.500 -0.3886 0.01972 0.01079 -0.0076 0.8315 0.4644
-3.250 -0.3625 0.01948 0.01053 -0.0071 0.8193 0.4766
-3.000 -0.3338 0.01922 0.01032 -0.0069 0.8078 0.4877
-2.750 -0.3091 0.01903 0.01010 -0.0061 0.7942 0.5001
-2.500 -0.2791 0.01879 0.00990 -0.0061 0.7831 0.5117
-2.250 -0.2535 0.01862 0.00972 -0.0054 0.7695 0.5240
-2.000 -0.2261 0.01846 0.00957 -0.0050 0.7570 0.5364
-1.750 -0.1975 0.01829 0.00939 -0.0047 0.7447 0.5486
-1.500 -0.1724 0.01820 0.00927 -0.0040 0.7312 0.5621
-1.250 -0.1430 0.01808 0.00916 -0.0038 0.7195 0.5743
-1.000 -0.1186 0.01802 0.00909 -0.0029 0.7055 0.5877
-0.750 -0.0912 0.01797 0.00904 -0.0025 0.6931 0.6007
-0.500 -0.0650 0.01794 0.00901 -0.0018 0.6798 0.6136
-0.250 -0.0399 0.01792 0.00897 -0.0010 0.6669 0.6276
0.000 -0.0120 0.01790 0.00896 -0.0006 0.6543 0.6399
0.250 0.0119 0.01790 0.00896 0.0003 0.6406 0.6537
0.500 0.0402 0.01792 0.00896 0.0007 0.6284 0.6662
0.750 0.0649 0.01793 0.00901 0.0015 0.6144 0.6793
1.000 0.0914 0.01797 0.00904 0.0021 0.6016 0.6925
1.250 0.1185 0.01802 0.00910 0.0026 0.5885 0.7051
1.500 0.1432 0.01808 0.00916 0.0034 0.5752 0.7190
1.750 0.1726 0.01819 0.00926 0.0036 0.5631 0.7308
2.000 0.1974 0.01829 0.00939 0.0044 0.5495 0.7444
2.250 0.2262 0.01845 0.00956 0.0046 0.5374 0.7566
2.500 0.2534 0.01861 0.00972 0.0051 0.5249 0.7693
2.750 0.2793 0.01878 0.00989 0.0057 0.5128 0.7829
3.000 0.3090 0.01902 0.01010 0.0058 0.5010 0.7940
3.250 0.3338 0.01921 0.01032 0.0066 0.4888 0.8077
3.500 0.3627 0.01947 0.01051 0.0067 0.4778 0.8192
3.750 0.3887 0.01971 0.01079 0.0073 0.4655 0.8315
4.000 0.4133 0.01994 0.01095 0.0081 0.4550 0.8449
4.250 0.4432 0.02024 0.01128 0.0080 0.4425 0.8547
4.500 0.4655 0.02048 0.01146 0.0092 0.4323 0.8686
4.750 0.4984 0.02083 0.01181 0.0084 0.4198 0.8767
5.000 0.5213 0.02109 0.01205 0.0094 0.4086 0.8899
5.250 0.5556 0.02147 0.01235 0.0083 0.3960 0.8972
5.500 0.5785 0.02176 0.01266 0.0092 0.3834 0.9098
5.750 0.6145 0.02216 0.01300 0.0076 0.3705 0.9162
6.000 0.6381 0.02247 0.01330 0.0083 0.3589 0.9281
6.250 0.6762 0.02288 0.01370 0.0061 0.3463 0.9334
6.500 0.7085 0.02328 0.01400 0.0049 0.3356 0.9414
6.750 0.7403 0.02366 0.01444 0.0038 0.3239 0.9492
7.000 0.7744 0.02408 0.01481 0.0022 0.3132 0.9559
7.250 0.8034 0.02449 0.01522 0.0015 0.3025 0.9643
7.500 0.8381 0.02494 0.01566 -0.0004 0.2920 0.9705
7.750 0.8667 0.02541 0.01609 -0.0011 0.2821 0.9784
8.000 0.9011 0.02588 0.01659 -0.0031 0.2716 0.9842
8.250 0.9304 0.02642 0.01705 -0.0042 0.2624 0.9913
8.500 0.9632 0.02692 0.01762 -0.0060 0.2520 0.9967
8.750 0.9810 0.02744 0.01806 -0.0050 0.2446 1.0000
9.000 0.9830 0.02782 0.01850 -0.0010 0.2381 1.0000
9.250 0.9819 0.02822 0.01890 0.0036 0.2323 1.0000
9.500 0.9756 0.02861 0.01921 0.0090 0.2278 1.0000
9.750 0.9706 0.02901 0.01967 0.0142 0.2224 1.0000
10.000 0.9662 0.02947 0.02016 0.0191 0.2172 1.0000
10.250 0.9629 0.03002 0.02064 0.0236 0.2125 1.0000
10.500 0.9626 0.03064 0.02128 0.0275 0.2072 1.0000
10.750 0.9631 0.03134 0.02201 0.0311 0.2017 1.0000
11.000 0.9642 0.03211 0.02272 0.0343 0.1970 1.0000
11.250 0.9673 0.03297 0.02362 0.0372 0.1919 1.0000
11.500 0.9707 0.03393 0.02462 0.0397 0.1865 1.0000
11.750 0.9748 0.03495 0.02559 0.0419 0.1821 1.0000
12.000 0.9799 0.03609 0.02678 0.0438 0.1772 1.0000
12.250 0.9846 0.03733 0.02807 0.0455 0.1724 1.0000
12.500 0.9896 0.03859 0.02931 0.0470 0.1684 1.0000
12.750 0.9947 0.04002 0.03079 0.0483 0.1641 1.0000
13.000 0.9990 0.04158 0.03242 0.0494 0.1597 1.0000
13.250 1.0036 0.04313 0.03396 0.0504 0.1561 1.0000
13.500 1.0083 0.04480 0.03566 0.0512 0.1525 1.0000
13.750 1.0109 0.04675 0.03771 0.0519 0.1485 1.0000
14.000 1.0142 0.04866 0.03964 0.0524 0.1451 1.0000
14.250 1.0199 0.05035 0.04127 0.0529 0.1421 1.0000
14.500 1.0192 0.05286 0.04395 0.0530 0.1386 1.0000
14.750 1.0197 0.05527 0.04644 0.0531 0.1353 1.0000
15.000 1.0228 0.05742 0.04859 0.0532 0.1325 1.0000
15.250 1.0252 0.05974 0.05094 0.0531 0.1297 1.0000
15.500 1.0206 0.06302 0.05437 0.0526 0.1267 1.0000
15.750 1.0190 0.06597 0.05740 0.0521 0.1238 1.0000
16.000 1.0228 0.06826 0.05967 0.0518 0.1213 1.0000
16.250 1.0206 0.07141 0.06290 0.0512 0.1189 1.0000
16.500 1.0097 0.07588 0.06756 0.0498 0.1163 1.0000
16.750 1.0039 0.07970 0.07147 0.0486 0.1137 1.0000
17.000 1.0074 0.08224 0.07400 0.0479 0.1115 1.0000
17.250 1.0038 0.08586 0.07769 0.0468 0.1093 1.0000
17.500 0.9767 0.09320 0.08529 0.0436 0.1069 1.0000
17.750 0.9561 0.09975 0.09201 0.0407 0.1045 1.0000
18.000 0.9571 0.10291 0.09518 0.0395 0.1025 1.0000
18.250 0.9676 0.10451 0.09673 0.0391 0.1007 1.0000
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