GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 100,000 Max Cl/Cd: 51.82 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe493-il-100000.txt Download as CSV file: xf-goe493-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4719 0.09959 0.09468 -0.0602 1.0000 0.0824
-11.250 -0.5979 0.07518 0.07030 -0.0729 1.0000 0.0706
-11.000 -0.6264 0.07110 0.06624 -0.0724 1.0000 0.0702
-10.750 -0.6600 0.06765 0.06278 -0.0710 1.0000 0.0697
-10.500 -0.6929 0.06525 0.06039 -0.0681 1.0000 0.0692
-10.250 -0.7301 0.06321 0.05831 -0.0635 1.0000 0.0688
-10.000 -0.7596 0.06026 0.05524 -0.0600 1.0000 0.0684
-9.750 -0.7854 0.05684 0.05162 -0.0567 1.0000 0.0681
-9.500 -0.8059 0.05314 0.04761 -0.0537 1.0000 0.0681
-9.250 -0.8190 0.04947 0.04357 -0.0509 1.0000 0.0683
-9.000 -0.8259 0.04593 0.03957 -0.0484 1.0000 0.0690
-8.750 -0.8281 0.04284 0.03588 -0.0459 1.0000 0.0705
-8.500 -0.8197 0.04051 0.03347 -0.0443 1.0000 0.0727
-8.250 -0.8072 0.03946 0.03240 -0.0428 1.0000 0.0758
-8.000 -0.7968 0.03755 0.03015 -0.0411 1.0000 0.0791
-7.750 -0.7860 0.03537 0.02743 -0.0393 1.0000 0.0825
-7.500 -0.7516 0.03434 0.02648 -0.0417 0.9948 0.0897
-7.250 -0.7206 0.03280 0.02470 -0.0434 0.9890 0.0981
-7.000 -0.6861 0.03176 0.02342 -0.0455 0.9835 0.1098
-6.750 -0.6575 0.03094 0.02244 -0.0465 0.9769 0.1229
-6.500 -0.6233 0.03026 0.02177 -0.0485 0.9713 0.1388
-6.250 -0.5963 0.02969 0.02115 -0.0492 0.9643 0.1541
-6.000 -0.5626 0.02924 0.02070 -0.0510 0.9583 0.1709
-5.750 -0.5348 0.02880 0.02020 -0.0516 0.9515 0.1861
-5.500 -0.5038 0.02840 0.01976 -0.0528 0.9450 0.2022
-5.250 -0.4704 0.02808 0.01944 -0.0544 0.9394 0.2189
-5.000 -0.4457 0.02769 0.01902 -0.0543 0.9318 0.2341
-4.750 -0.4074 0.02738 0.01875 -0.0566 0.9268 0.2539
-4.500 -0.3867 0.02703 0.01844 -0.0558 0.9187 0.2711
-4.250 -0.3532 0.02672 0.01818 -0.0572 0.9129 0.2961
-4.000 -0.3262 0.02650 0.01805 -0.0573 0.9062 0.3247
-3.750 -0.3000 0.02625 0.01798 -0.0574 0.8990 0.3588
-3.500 -0.2620 0.02617 0.01808 -0.0593 0.8947 0.4065
-3.250 -0.2490 0.02618 0.01823 -0.0569 0.8853 0.4409
-3.000 -0.2142 0.02626 0.01842 -0.0580 0.8801 0.4853
-2.750 -0.1966 0.02644 0.01867 -0.0563 0.8719 0.5173
-2.500 -0.1674 0.02657 0.01884 -0.0564 0.8658 0.5511
-2.250 -0.1344 0.02670 0.01900 -0.0571 0.8608 0.5833
-2.000 -0.1197 0.02688 0.01921 -0.0549 0.8517 0.6085
-1.750 -0.0836 0.02692 0.01929 -0.0560 0.8475 0.6388
-1.500 -0.0728 0.02721 0.01965 -0.0532 0.8386 0.6607
-1.250 -0.0414 0.02727 0.01974 -0.0534 0.8332 0.6899
-1.000 -0.0196 0.02746 0.02001 -0.0522 0.8265 0.7151
-0.750 0.0009 0.02764 0.02023 -0.0508 0.8193 0.7423
-0.500 0.0373 0.02756 0.02020 -0.0517 0.8156 0.7726
-0.250 0.0446 0.02793 0.02065 -0.0483 0.8059 0.7986
0.000 0.0779 0.02786 0.02064 -0.0488 0.8014 0.8331
0.250 0.1155 0.02779 0.02066 -0.0501 0.7973 0.8740
0.500 0.1574 0.02823 0.02121 -0.0536 0.7891 0.9225
0.750 0.2480 0.02828 0.02125 -0.0655 0.7866 0.9645
1.250 0.3261 0.02828 0.02100 -0.0723 0.7721 1.0000
1.500 0.3763 0.02762 0.02024 -0.0758 0.7686 1.0000
1.750 0.3813 0.02819 0.02070 -0.0726 0.7567 1.0000
2.000 0.4288 0.02761 0.02006 -0.0754 0.7533 1.0000
2.250 0.4837 0.02682 0.01923 -0.0794 0.7516 1.0000
2.500 0.4769 0.02796 0.02031 -0.0744 0.7384 1.0000
2.750 0.5303 0.02712 0.01946 -0.0779 0.7366 1.0000
3.000 0.5262 0.02830 0.02060 -0.0734 0.7237 1.0000
3.250 0.5790 0.02739 0.01970 -0.0767 0.7216 1.0000
3.500 0.6376 0.02644 0.01877 -0.0811 0.7199 1.0000
3.750 0.6301 0.02760 0.01992 -0.0757 0.7068 1.0000
4.000 0.6352 0.02850 0.02082 -0.0724 0.6955 1.0000
4.250 0.6848 0.02765 0.02001 -0.0752 0.6920 1.0000
4.500 0.7445 0.02654 0.01897 -0.0795 0.6896 1.0000
4.750 0.7463 0.02741 0.01985 -0.0754 0.6774 1.0000
5.000 0.8037 0.02638 0.01891 -0.0795 0.6743 1.0000
5.250 0.8104 0.02713 0.01970 -0.0762 0.6627 1.0000
5.500 0.8682 0.02603 0.01868 -0.0802 0.6586 1.0000
5.750 0.8793 0.02660 0.01931 -0.0774 0.6470 1.0000
6.000 0.9370 0.02559 0.01839 -0.0815 0.6423 1.0000
6.250 0.9462 0.02625 0.01913 -0.0784 0.6303 1.0000
6.500 0.9923 0.02556 0.01851 -0.0806 0.6219 1.0000
6.750 1.0406 0.02447 0.01746 -0.0828 0.6099 1.0000
7.000 1.0769 0.02355 0.01655 -0.0830 0.5935 1.0000
7.250 1.0951 0.02314 0.01615 -0.0803 0.5743 1.0000
7.500 1.1115 0.02272 0.01572 -0.0774 0.5534 1.0000
7.750 1.1315 0.02232 0.01528 -0.0751 0.5326 1.0000
8.000 1.1498 0.02219 0.01513 -0.0728 0.5138 1.0000
8.250 1.1579 0.02241 0.01540 -0.0690 0.4960 1.0000
8.500 1.1628 0.02266 0.01571 -0.0648 0.4781 1.0000
8.750 1.1659 0.02298 0.01607 -0.0603 0.4589 1.0000
9.000 1.1695 0.02332 0.01641 -0.0560 0.4369 1.0000
9.250 1.1673 0.02391 0.01701 -0.0511 0.4112 1.0000
9.500 1.1621 0.02472 0.01772 -0.0461 0.3790 1.0000
9.750 1.1513 0.02598 0.01877 -0.0407 0.3365 1.0000
10.000 1.1316 0.02802 0.02047 -0.0349 0.2763 1.0000
10.250 1.1048 0.03102 0.02288 -0.0294 0.1947 1.0000
10.500 1.0814 0.03442 0.02575 -0.0251 0.1541 1.0000
10.750 1.0673 0.03746 0.02852 -0.0218 0.1333 1.0000
11.000 1.0629 0.03991 0.03085 -0.0194 0.1196 1.0000
11.250 1.0658 0.04188 0.03281 -0.0176 0.1095 1.0000
11.500 1.0713 0.04372 0.03458 -0.0159 0.1021 1.0000
11.750 1.0820 0.04522 0.03605 -0.0145 0.0962 1.0000
12.000 1.1022 0.04634 0.03705 -0.0133 0.0908 1.0000
12.250 1.1219 0.04750 0.03825 -0.0124 0.0858 1.0000
12.500 1.1653 0.04833 0.03883 -0.0127 0.0803 1.0000
12.750 1.1851 0.04986 0.04060 -0.0119 0.0772 1.0000
13.000 1.2056 0.05147 0.04233 -0.0113 0.0738 1.0000
13.250 1.2722 0.05394 0.04461 -0.0142 0.0691 1.0000
13.500 1.2736 0.05605 0.04706 -0.0122 0.0681 1.0000
13.750 1.2743 0.05845 0.04978 -0.0104 0.0667 1.0000
14.000 1.2760 0.06112 0.05274 -0.0088 0.0653 1.0000
14.250 1.2767 0.06413 0.05604 -0.0074 0.0644 1.0000
14.500 1.2736 0.06742 0.05961 -0.0060 0.0638 1.0000
14.750 1.2664 0.07092 0.06338 -0.0047 0.0633 1.0000
15.000 1.2557 0.07467 0.06740 -0.0036 0.0628 1.0000
15.250 1.2443 0.07847 0.07143 -0.0028 0.0622 1.0000
15.500 1.2242 0.08312 0.07635 -0.0023 0.0622 1.0000
15.750 1.1984 0.08844 0.08197 -0.0025 0.0625 1.0000
16.000 1.1671 0.09477 0.08861 -0.0037 0.0630 1.0000
16.250 1.1314 0.10224 0.09637 -0.0060 0.0639 1.0000
16.500 1.0934 0.11092 0.10530 -0.0097 0.0651 1.0000
16.750 1.0549 0.12072 0.11530 -0.0148 0.0663 1.0000
17.000 1.0204 0.13118 0.12588 -0.0205 0.0676 1.0000
17.250 0.9991 0.14034 0.13511 -0.0252 0.0687 1.0000
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