GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 386 AIRFOIL (goe386-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.65 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe386-il-1000000.txt Download as CSV file: xf-goe386-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 386 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.8856 0.08149 0.07830 -0.0874 1.0000 0.0426
-18.500 -0.9125 0.07415 0.07082 -0.0923 1.0000 0.0427
-18.250 -0.9377 0.06748 0.06402 -0.0967 1.0000 0.0429
-18.000 -0.9607 0.06163 0.05807 -0.1002 1.0000 0.0432
-17.750 -0.9760 0.05665 0.05301 -0.1033 1.0000 0.0434
-17.500 -0.9883 0.05192 0.04822 -0.1063 1.0000 0.0436
-17.250 -0.9977 0.04753 0.04375 -0.1092 1.0000 0.0438
-17.000 -1.0046 0.04347 0.03962 -0.1119 1.0000 0.0440
-16.750 -1.0107 0.03988 0.03596 -0.1140 1.0000 0.0442
-16.500 -1.0143 0.03674 0.03275 -0.1159 0.9990 0.0444
-16.250 -0.9970 0.03394 0.02988 -0.1202 0.9952 0.0447
-16.000 -0.9776 0.03158 0.02746 -0.1241 0.9913 0.0451
-15.750 -0.9612 0.02959 0.02539 -0.1267 0.9827 0.0454
-15.500 -0.9452 0.02789 0.02361 -0.1285 0.9728 0.0458
-15.250 -0.9335 0.02645 0.02207 -0.1289 0.9605 0.0461
-15.000 -0.9242 0.02528 0.02080 -0.1282 0.9480 0.0464
-14.750 -0.9135 0.02428 0.01971 -0.1272 0.9375 0.0466
-14.500 -0.9019 0.02345 0.01876 -0.1259 0.9278 0.0469
-14.250 -0.8878 0.02273 0.01795 -0.1248 0.9191 0.0471
-14.000 -0.8731 0.02214 0.01726 -0.1233 0.9104 0.0473
-13.750 -0.8660 0.02109 0.01614 -0.1211 0.9022 0.0478
-13.500 -0.8494 0.02043 0.01543 -0.1199 0.8943 0.0482
-13.250 -0.8297 0.01994 0.01490 -0.1189 0.8874 0.0486
-13.000 -0.8082 0.01950 0.01443 -0.1182 0.8803 0.0490
-12.750 -0.7863 0.01912 0.01400 -0.1174 0.8727 0.0493
-12.500 -0.7637 0.01873 0.01356 -0.1167 0.8655 0.0497
-12.250 -0.7405 0.01836 0.01315 -0.1161 0.8571 0.0502
-12.000 -0.7171 0.01803 0.01274 -0.1154 0.8480 0.0507
-11.750 -0.6929 0.01769 0.01234 -0.1149 0.8385 0.0512
-11.500 -0.6690 0.01738 0.01193 -0.1142 0.8270 0.0517
-11.250 -0.6443 0.01708 0.01156 -0.1137 0.8134 0.0520
-11.000 -0.6222 0.01656 0.01093 -0.1128 0.7967 0.0525
-10.750 -0.6000 0.01610 0.01039 -0.1120 0.7742 0.0531
-10.500 -0.5767 0.01589 0.01005 -0.1111 0.7444 0.0535
-10.250 -0.5529 0.01575 0.00977 -0.1103 0.7088 0.0540
-10.000 -0.5288 0.01564 0.00951 -0.1096 0.6783 0.0545
-9.750 -0.5040 0.01549 0.00925 -0.1090 0.6564 0.0550
-9.250 -0.4526 0.01516 0.00875 -0.1081 0.6288 0.0562
-9.000 -0.4265 0.01504 0.00853 -0.1077 0.6180 0.0568
-8.750 -0.3992 0.01491 0.00834 -0.1074 0.6111 0.0573
-8.500 -0.3753 0.01443 0.00782 -0.1068 0.6041 0.0580
-8.250 -0.3498 0.01421 0.00755 -0.1063 0.5966 0.0587
-8.000 -0.3225 0.01400 0.00734 -0.1061 0.5925 0.0592
-7.750 -0.2953 0.01382 0.00714 -0.1059 0.5877 0.0599
-7.500 -0.2682 0.01367 0.00695 -0.1056 0.5827 0.0606
-7.250 -0.2414 0.01354 0.00677 -0.1053 0.5771 0.0613
-7.000 -0.2137 0.01340 0.00659 -0.1051 0.5733 0.0620
-6.750 -0.1853 0.01329 0.00645 -0.1050 0.5697 0.0626
-6.500 -0.1590 0.01298 0.00612 -0.1046 0.5654 0.0634
-6.250 -0.1326 0.01273 0.00584 -0.1043 0.5611 0.0642
-6.000 -0.1057 0.01260 0.00568 -0.1040 0.5560 0.0650
-5.750 -0.0780 0.01246 0.00553 -0.1038 0.5526 0.0658
-5.500 -0.0498 0.01230 0.00537 -0.1037 0.5500 0.0666
-5.250 -0.0215 0.01217 0.00522 -0.1036 0.5472 0.0675
-5.000 0.0068 0.01208 0.00511 -0.1035 0.5440 0.0683
-4.750 0.0347 0.01197 0.00496 -0.1034 0.5408 0.0690
-4.500 0.0608 0.01169 0.00467 -0.1030 0.5372 0.0702
-4.250 0.0880 0.01159 0.00454 -0.1027 0.5328 0.0711
-4.000 0.1165 0.01144 0.00440 -0.1027 0.5309 0.0721
-3.750 0.1450 0.01131 0.00428 -0.1026 0.5285 0.0732
-3.500 0.1735 0.01121 0.00417 -0.1026 0.5258 0.0743
-3.250 0.2020 0.01115 0.00409 -0.1025 0.5229 0.0751
-3.000 0.2292 0.01095 0.00387 -0.1023 0.5197 0.0765
-2.750 0.2566 0.01085 0.00375 -0.1021 0.5161 0.0779
-2.500 0.2843 0.01080 0.00367 -0.1019 0.5123 0.0791
-2.250 0.3131 0.01069 0.00358 -0.1019 0.5106 0.0805
-2.000 0.3418 0.01061 0.00351 -0.1020 0.5083 0.0818
-1.750 0.3701 0.01048 0.00338 -0.1019 0.5057 0.0838
-1.500 0.3983 0.01038 0.00329 -0.1018 0.5029 0.0859
-1.250 0.4264 0.01032 0.00322 -0.1017 0.5001 0.0880
-1.000 0.4542 0.01028 0.00317 -0.1016 0.4969 0.0908
-0.750 0.4815 0.01024 0.00313 -0.1014 0.4931 0.0969
-0.500 0.5087 0.00996 0.00310 -0.1013 0.4911 0.1521
-0.250 0.5374 0.00988 0.00310 -0.1013 0.4887 0.1700
0.000 0.5659 0.00983 0.00310 -0.1014 0.4856 0.1828
0.250 0.5941 0.00981 0.00310 -0.1013 0.4820 0.1930
0.500 0.6217 0.00981 0.00311 -0.1012 0.4781 0.2037
0.750 0.6487 0.00984 0.00316 -0.1010 0.4736 0.2156
1.000 0.6774 0.00980 0.00317 -0.1010 0.4709 0.2280
1.250 0.7057 0.00975 0.00319 -0.1011 0.4674 0.2455
1.500 0.7334 0.00971 0.00321 -0.1010 0.4629 0.2677
1.750 0.7601 0.00968 0.00326 -0.1008 0.4579 0.2996
2.000 0.7869 0.00963 0.00332 -0.1006 0.4530 0.3399
2.250 0.8145 0.00954 0.00337 -0.1006 0.4475 0.3874
2.500 0.8405 0.00948 0.00343 -0.1002 0.4400 0.4444
2.750 0.8660 0.00936 0.00352 -0.0999 0.4325 0.5270
3.000 0.8905 0.00918 0.00363 -0.0994 0.4225 0.6425
3.250 0.9127 0.00900 0.00379 -0.0982 0.4114 0.7752
3.500 0.9318 0.00899 0.00399 -0.0963 0.3965 0.8764
3.750 0.9510 0.00918 0.00422 -0.0944 0.3787 0.9404
4.000 0.9808 0.00954 0.00448 -0.0949 0.3603 0.9765
4.250 1.0185 0.00993 0.00476 -0.0972 0.3454 0.9936
4.500 1.0520 0.01027 0.00502 -0.0987 0.3348 1.0000
4.750 1.0675 0.01049 0.00518 -0.0964 0.3280 1.0000
5.000 1.0839 0.01070 0.00535 -0.0942 0.3226 1.0000
5.250 1.1006 0.01097 0.00558 -0.0921 0.3173 1.0000
5.500 1.1201 0.01122 0.00580 -0.0907 0.3129 1.0000
5.750 1.1419 0.01142 0.00599 -0.0897 0.3100 1.0000
6.000 1.1631 0.01167 0.00622 -0.0886 0.3064 1.0000
6.250 1.1831 0.01198 0.00650 -0.0874 0.3025 1.0000
6.500 1.2013 0.01238 0.00685 -0.0859 0.2977 1.0000
6.750 1.2242 0.01261 0.00709 -0.0853 0.2954 1.0000
7.000 1.2469 0.01286 0.00734 -0.0846 0.2931 1.0000
7.250 1.2686 0.01315 0.00763 -0.0838 0.2906 1.0000
7.500 1.2894 0.01348 0.00796 -0.0829 0.2882 1.0000
7.750 1.3090 0.01389 0.00834 -0.0818 0.2855 1.0000
8.000 1.3270 0.01437 0.00880 -0.0806 0.2822 1.0000
8.250 1.3460 0.01481 0.00925 -0.0796 0.2797 1.0000
8.500 1.3682 0.01512 0.00958 -0.0790 0.2785 1.0000
8.750 1.3900 0.01546 0.00994 -0.0784 0.2768 1.0000
9.000 1.4108 0.01585 0.01034 -0.0777 0.2749 1.0000
9.250 1.4304 0.01630 0.01080 -0.0769 0.2727 1.0000
9.500 1.4490 0.01682 0.01131 -0.0760 0.2703 1.0000
9.750 1.4653 0.01746 0.01195 -0.0748 0.2677 1.0000
10.000 1.4797 0.01822 0.01270 -0.0735 0.2647 1.0000
10.250 1.4988 0.01875 0.01326 -0.0728 0.2632 1.0000
10.500 1.5192 0.01921 0.01375 -0.0722 0.2617 1.0000
10.750 1.5389 0.01971 0.01429 -0.0717 0.2599 1.0000
11.000 1.5567 0.02034 0.01493 -0.0709 0.2579 1.0000
11.250 1.5734 0.02103 0.01564 -0.0701 0.2558 1.0000
11.500 1.5885 0.02185 0.01647 -0.0691 0.2538 1.0000
11.750 1.6016 0.02281 0.01744 -0.0680 0.2516 1.0000
12.000 1.6117 0.02396 0.01859 -0.0667 0.2490 1.0000
12.250 1.6278 0.02476 0.01943 -0.0660 0.2476 1.0000
12.500 1.6450 0.02551 0.02024 -0.0654 0.2464 1.0000
12.750 1.6607 0.02638 0.02115 -0.0648 0.2448 1.0000
13.000 1.6762 0.02728 0.02209 -0.0642 0.2430 1.0000
13.250 1.6890 0.02840 0.02324 -0.0635 0.2410 1.0000
13.500 1.7004 0.02964 0.02450 -0.0627 0.2386 1.0000
13.750 1.7079 0.03123 0.02610 -0.0617 0.2358 1.0000
14.000 1.7151 0.03288 0.02776 -0.0608 0.2331 1.0000
14.250 1.7303 0.03391 0.02886 -0.0604 0.2316 1.0000
14.500 1.7431 0.03518 0.03018 -0.0600 0.2297 1.0000
14.750 1.7542 0.03656 0.03160 -0.0595 0.2274 1.0000
15.000 1.7618 0.03830 0.03337 -0.0589 0.2247 1.0000
15.250 1.7660 0.04037 0.03546 -0.0582 0.2217 1.0000
15.500 1.7698 0.04247 0.03759 -0.0575 0.2187 1.0000
15.750 1.7808 0.04397 0.03915 -0.0572 0.2167 1.0000
16.000 1.7900 0.04559 0.04082 -0.0568 0.2141 1.0000
16.250 1.7942 0.04772 0.04298 -0.0564 0.2111 1.0000
16.500 1.7948 0.05019 0.04547 -0.0558 0.2076 1.0000
16.750 1.7964 0.05260 0.04791 -0.0553 0.2045 1.0000
17.000 1.8043 0.05437 0.04974 -0.0550 0.2015 1.0000
17.250 1.8056 0.05683 0.05223 -0.0546 0.1977 1.0000
17.500 1.8009 0.05988 0.05529 -0.0540 0.1933 1.0000
17.750 1.8031 0.06227 0.05773 -0.0537 0.1895 1.0000
18.000 1.8030 0.06490 0.06038 -0.0534 0.1845 1.0000
18.250 1.7935 0.06857 0.06406 -0.0530 0.1793 1.0000
18.500 1.7946 0.07110 0.06663 -0.0528 0.1745 1.0000
18.750 1.7841 0.07494 0.07047 -0.0526 0.1687 1.0000
19.000 1.7792 0.07819 0.07376 -0.0525 0.1635 1.0000
19.250 1.7681 0.08216 0.07774 -0.0524 0.1576 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 386 AIRFOIL (goe386-il)