GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 100,000 Max Cl/Cd: 48.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe676-il-100000-n5.txt Download as CSV file: xf-goe676-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5687 0.09105 0.08585 -0.0285 1.0000 0.0459
-10.250 -0.5893 0.08051 0.07533 -0.0370 1.0000 0.0460
-10.000 -0.6168 0.07130 0.06606 -0.0440 1.0000 0.0459
-9.750 -0.6458 0.06515 0.05977 -0.0454 1.0000 0.0459
-9.500 -0.6730 0.05939 0.05374 -0.0447 1.0000 0.0462
-9.000 -0.6903 0.05143 0.04529 -0.0415 1.0000 0.0475
-8.750 -0.6838 0.04926 0.04302 -0.0400 1.0000 0.0483
-8.500 -0.6791 0.04677 0.04034 -0.0381 1.0000 0.0489
-8.250 -0.6741 0.04437 0.03774 -0.0360 1.0000 0.0498
-8.000 -0.6679 0.04230 0.03546 -0.0336 1.0000 0.0511
-7.750 -0.6626 0.04002 0.03289 -0.0310 1.0000 0.0526
-7.500 -0.6573 0.03762 0.03011 -0.0281 1.0000 0.0539
-7.250 -0.6500 0.03534 0.02744 -0.0253 1.0000 0.0548
-7.000 -0.6406 0.03335 0.02504 -0.0227 1.0000 0.0556
-6.750 -0.6293 0.03174 0.02302 -0.0202 1.0000 0.0566
-6.500 -0.6082 0.03015 0.02136 -0.0199 0.9978 0.0583
-6.250 -0.5751 0.02886 0.01993 -0.0217 0.9923 0.0604
-6.000 -0.5416 0.02741 0.01825 -0.0234 0.9865 0.0622
-5.750 -0.5077 0.02603 0.01661 -0.0249 0.9809 0.0640
-5.500 -0.4728 0.02478 0.01512 -0.0266 0.9752 0.0661
-5.250 -0.4376 0.02385 0.01395 -0.0282 0.9693 0.0688
-5.000 -0.4034 0.02268 0.01282 -0.0299 0.9633 0.0721
-4.750 -0.3677 0.02179 0.01190 -0.0318 0.9579 0.0754
-4.500 -0.3352 0.02098 0.01102 -0.0328 0.9501 0.0788
-4.250 -0.3008 0.02022 0.01016 -0.0342 0.9437 0.0826
-4.000 -0.2714 0.01951 0.00954 -0.0348 0.9347 0.0882
-3.750 -0.2398 0.01897 0.00895 -0.0356 0.9265 0.0955
-3.500 -0.2103 0.01839 0.00844 -0.0361 0.9173 0.1031
-3.250 -0.1819 0.01793 0.00801 -0.0362 0.9074 0.1138
-3.000 -0.1510 0.01746 0.00759 -0.0368 0.8991 0.1306
-2.750 -0.1244 0.01703 0.00720 -0.0365 0.8878 0.1544
-2.500 -0.0978 0.01642 0.00679 -0.0363 0.8774 0.1944
-2.250 -0.0724 0.01545 0.00641 -0.0360 0.8680 0.3134
-2.000 -0.0541 0.01432 0.00626 -0.0341 0.8559 0.5416
-1.750 -0.0266 0.01380 0.00653 -0.0324 0.8456 0.7442
-1.500 0.0113 0.01392 0.00674 -0.0326 0.8365 0.8435
-1.250 0.0434 0.01416 0.00691 -0.0322 0.8244 0.8978
-1.000 0.0896 0.01444 0.00707 -0.0345 0.8131 0.9350
-0.750 0.1417 0.01458 0.00705 -0.0386 0.8017 0.9596
-0.500 0.1881 0.01456 0.00687 -0.0421 0.7896 0.9728
-0.250 0.2338 0.01450 0.00669 -0.0457 0.7759 0.9845
0.000 0.2797 0.01440 0.00648 -0.0495 0.7621 0.9949
0.250 0.3151 0.01431 0.00630 -0.0513 0.7482 1.0000
0.500 0.3385 0.01427 0.00617 -0.0505 0.7345 1.0000
0.750 0.3621 0.01425 0.00607 -0.0498 0.7212 1.0000
1.000 0.3857 0.01423 0.00597 -0.0490 0.7079 1.0000
1.250 0.4093 0.01423 0.00589 -0.0482 0.6949 1.0000
1.500 0.4328 0.01425 0.00584 -0.0474 0.6819 1.0000
1.750 0.4562 0.01430 0.00582 -0.0466 0.6685 1.0000
2.000 0.4797 0.01436 0.00584 -0.0458 0.6554 1.0000
2.250 0.5031 0.01444 0.00586 -0.0450 0.6424 1.0000
2.500 0.5265 0.01454 0.00590 -0.0441 0.6296 1.0000
2.750 0.5497 0.01466 0.00597 -0.0432 0.6161 1.0000
3.000 0.5727 0.01479 0.00604 -0.0423 0.6017 1.0000
3.250 0.5954 0.01493 0.00614 -0.0413 0.5866 1.0000
3.500 0.6180 0.01508 0.00628 -0.0403 0.5709 1.0000
3.750 0.6404 0.01524 0.00642 -0.0393 0.5551 1.0000
4.250 0.6848 0.01559 0.00675 -0.0371 0.5231 1.0000
4.500 0.7068 0.01578 0.00694 -0.0361 0.5077 1.0000
4.750 0.7286 0.01599 0.00714 -0.0349 0.4917 1.0000
5.000 0.7501 0.01621 0.00735 -0.0338 0.4750 1.0000
5.250 0.7716 0.01646 0.00760 -0.0326 0.4596 1.0000
5.500 0.7931 0.01674 0.00787 -0.0315 0.4451 1.0000
5.750 0.8141 0.01703 0.00815 -0.0302 0.4292 1.0000
6.000 0.8349 0.01734 0.00848 -0.0290 0.4137 1.0000
6.250 0.8558 0.01768 0.00883 -0.0278 0.3999 1.0000
6.500 0.8766 0.01803 0.00921 -0.0265 0.3855 1.0000
6.750 0.8970 0.01840 0.00961 -0.0253 0.3702 1.0000
7.000 0.9171 0.01879 0.01006 -0.0240 0.3543 1.0000
7.250 0.9370 0.01920 0.01052 -0.0227 0.3380 1.0000
7.500 0.9561 0.01964 0.01102 -0.0213 0.3172 1.0000
7.750 0.9731 0.02018 0.01151 -0.0196 0.2895 1.0000
8.000 0.9884 0.02082 0.01208 -0.0179 0.2520 1.0000
8.250 1.0020 0.02163 0.01271 -0.0159 0.2117 1.0000
8.500 1.0151 0.02256 0.01348 -0.0140 0.1810 1.0000
9.000 1.0397 0.02458 0.01531 -0.0102 0.1449 1.0000
9.500 1.0614 0.02674 0.01748 -0.0061 0.1189 1.0000
9.750 1.0714 0.02781 0.01862 -0.0041 0.1066 1.0000
10.000 1.0790 0.02891 0.01979 -0.0017 0.0943 1.0000
10.250 1.0866 0.03008 0.02101 0.0005 0.0819 1.0000
10.500 1.0932 0.03137 0.02233 0.0025 0.0712 1.0000
10.750 1.0975 0.03290 0.02382 0.0044 0.0637 1.0000
11.000 1.1020 0.03452 0.02553 0.0061 0.0574 1.0000
11.250 1.1034 0.03648 0.02747 0.0077 0.0532 1.0000
11.500 1.1068 0.03840 0.02952 0.0090 0.0494 1.0000
11.750 1.1082 0.04058 0.03176 0.0101 0.0466 1.0000
12.000 1.1073 0.04306 0.03426 0.0111 0.0443 1.0000
12.250 1.1107 0.04528 0.03664 0.0119 0.0418 1.0000
12.500 1.1126 0.04769 0.03917 0.0124 0.0396 1.0000
12.750 1.1132 0.05030 0.04185 0.0128 0.0380 1.0000
13.000 1.1128 0.05307 0.04466 0.0132 0.0368 1.0000
13.250 1.1151 0.05568 0.04743 0.0137 0.0355 1.0000
13.500 1.1172 0.05840 0.05033 0.0139 0.0341 1.0000
13.750 1.1179 0.06131 0.05339 0.0138 0.0327 1.0000
14.000 1.1174 0.06438 0.05657 0.0136 0.0316 1.0000
14.250 1.1163 0.06756 0.05984 0.0132 0.0306 1.0000
14.500 1.1158 0.07069 0.06301 0.0130 0.0298 1.0000
14.750 1.1150 0.07400 0.06643 0.0128 0.0292 1.0000
15.000 1.1107 0.07801 0.07068 0.0119 0.0287 1.0000
15.250 1.1043 0.08245 0.07535 0.0106 0.0282 1.0000
15.500 1.0957 0.08734 0.08047 0.0089 0.0277 1.0000
15.750 1.0852 0.09274 0.08610 0.0067 0.0273 1.0000
16.000 1.0726 0.09871 0.09229 0.0040 0.0270 1.0000
16.250 1.0579 0.10533 0.09912 0.0006 0.0268 1.0000
16.500 1.0406 0.11279 0.10679 -0.0034 0.0266 1.0000
16.750 1.0192 0.12157 0.11578 -0.0085 0.0267 1.0000
17.000 0.9903 0.13278 0.12723 -0.0153 0.0270 1.0000
17.250 0.9467 0.14914 0.14379 -0.0251 0.0278 1.0000
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Polar data table (+)
Polar graphs
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