GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 100,000 Max Cl/Cd: 57.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe257-il-100000-n5.txt Download as CSV file: xf-goe257-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3806 0.09753 0.09287 -0.0193 1.0000 0.0387
-7.750 -0.3786 0.09441 0.08980 -0.0207 1.0000 0.0398
-7.500 -0.3754 0.09115 0.08659 -0.0231 1.0000 0.0411
-7.250 -0.3689 0.08761 0.08309 -0.0280 1.0000 0.0430
-7.000 -0.3546 0.08388 0.07931 -0.0391 1.0000 0.0445
-6.750 -0.3445 0.07906 0.07448 -0.0429 1.0000 0.0452
-6.500 -0.3435 0.07587 0.07143 -0.0368 1.0000 0.0475
-6.250 -0.3342 0.07289 0.06845 -0.0373 1.0000 0.0504
-6.000 -0.3217 0.06944 0.06496 -0.0402 1.0000 0.0537
-5.500 -0.2905 0.06139 0.05672 -0.0473 0.9997 0.0592
-5.250 -0.2625 0.05771 0.05302 -0.0503 0.9918 0.0639
-5.000 -0.2213 0.05284 0.04786 -0.0582 0.9831 0.0742
-4.750 -0.1739 0.04936 0.04379 -0.0659 0.9735 0.0863
-4.500 -0.1457 0.04487 0.03940 -0.0683 0.9620 0.0894
-4.000 -0.0576 0.03504 0.02832 -0.0761 0.9350 0.0556
-3.750 -0.0240 0.03188 0.02485 -0.0780 0.9172 0.0528
-3.500 0.0097 0.02951 0.02202 -0.0794 0.8993 0.0535
-3.250 0.0417 0.02745 0.01952 -0.0802 0.8819 0.0535
-3.000 0.0725 0.02556 0.01724 -0.0806 0.8645 0.0520
-2.750 0.1024 0.02398 0.01526 -0.0806 0.8471 0.0511
-2.500 0.1316 0.02266 0.01358 -0.0805 0.8299 0.0506
-2.250 0.1603 0.02156 0.01214 -0.0803 0.8140 0.0504
-2.000 0.1884 0.02077 0.01110 -0.0801 0.7993 0.0526
-1.750 0.2165 0.02003 0.01012 -0.0798 0.7860 0.0541
-1.500 0.2445 0.01927 0.00916 -0.0794 0.7738 0.0539
-1.250 0.2722 0.01863 0.00837 -0.0791 0.7622 0.0538
-1.000 0.2999 0.01808 0.00772 -0.0789 0.7508 0.0539
-0.750 0.3274 0.01762 0.00718 -0.0787 0.7404 0.0541
-0.500 0.3548 0.01726 0.00672 -0.0784 0.7310 0.0546
-0.250 0.3825 0.01699 0.00637 -0.0783 0.7209 0.0553
0.000 0.4103 0.01682 0.00608 -0.0782 0.7114 0.0563
0.500 0.4660 0.01659 0.00567 -0.0780 0.6922 0.0618
0.750 0.4943 0.01658 0.00558 -0.0780 0.6831 0.0700
1.000 0.5227 0.01654 0.00553 -0.0781 0.6742 0.0819
1.250 0.5479 0.01426 0.00548 -0.0777 0.6650 1.0000
1.500 0.5757 0.01445 0.00547 -0.0775 0.6553 1.0000
1.750 0.6033 0.01463 0.00551 -0.0774 0.6441 1.0000
2.000 0.6308 0.01480 0.00557 -0.0773 0.6319 1.0000
2.250 0.6583 0.01498 0.00565 -0.0772 0.6200 1.0000
2.500 0.6857 0.01515 0.00575 -0.0771 0.6084 1.0000
2.750 0.7130 0.01532 0.00584 -0.0770 0.5970 1.0000
3.000 0.7403 0.01549 0.00597 -0.0769 0.5846 1.0000
3.250 0.7675 0.01566 0.00614 -0.0768 0.5718 1.0000
3.500 0.7946 0.01583 0.00630 -0.0767 0.5583 1.0000
3.750 0.8217 0.01601 0.00647 -0.0766 0.5454 1.0000
4.000 0.8488 0.01621 0.00671 -0.0765 0.5339 1.0000
4.250 0.8757 0.01643 0.00693 -0.0764 0.5231 1.0000
4.500 0.9026 0.01665 0.00719 -0.0763 0.5113 1.0000
4.750 0.9293 0.01689 0.00747 -0.0762 0.4989 1.0000
5.000 0.9559 0.01715 0.00780 -0.0760 0.4863 1.0000
5.250 0.9821 0.01742 0.00812 -0.0758 0.4731 1.0000
5.500 1.0080 0.01772 0.00845 -0.0755 0.4582 1.0000
5.750 1.0333 0.01805 0.00883 -0.0751 0.4410 1.0000
6.000 1.0582 0.01843 0.00921 -0.0747 0.4225 1.0000
6.250 1.0826 0.01882 0.00967 -0.0742 0.3992 1.0000
6.500 1.1055 0.01928 0.01009 -0.0736 0.3638 1.0000
6.750 1.1278 0.01982 0.01058 -0.0729 0.3187 1.0000
7.000 1.1491 0.02052 0.01115 -0.0722 0.2790 1.0000
7.250 1.1690 0.02142 0.01191 -0.0713 0.2470 1.0000
7.500 1.1855 0.02272 0.01294 -0.0701 0.2019 1.0000
7.750 1.2026 0.02398 0.01403 -0.0689 0.1366 1.0000
8.000 1.2056 0.02680 0.01615 -0.0663 0.0517 1.0000
8.250 1.2188 0.02838 0.01777 -0.0644 0.0351 1.0000
8.500 1.2328 0.02975 0.01924 -0.0627 0.0290 1.0000
8.750 1.2449 0.03121 0.02084 -0.0608 0.0265 1.0000
9.000 1.2549 0.03271 0.02253 -0.0586 0.0247 1.0000
9.250 1.2617 0.03431 0.02430 -0.0562 0.0229 1.0000
9.500 1.2619 0.03618 0.02630 -0.0531 0.0215 1.0000
9.750 1.2576 0.03832 0.02858 -0.0497 0.0207 1.0000
10.000 1.2566 0.04046 0.03096 -0.0472 0.0201 1.0000
10.250 1.2547 0.04289 0.03358 -0.0451 0.0197 1.0000
10.500 1.2533 0.04550 0.03636 -0.0435 0.0194 1.0000
10.750 1.2528 0.04819 0.03920 -0.0421 0.0190 1.0000
11.000 1.2541 0.05085 0.04200 -0.0408 0.0187 1.0000
11.250 1.2577 0.05339 0.04468 -0.0394 0.0183 1.0000
11.500 1.2635 0.05584 0.04725 -0.0380 0.0179 1.0000
11.750 1.2695 0.05835 0.04992 -0.0368 0.0172 1.0000
12.000 1.2744 0.06104 0.05277 -0.0359 0.0165 1.0000
12.250 1.2775 0.06396 0.05587 -0.0351 0.0159 1.0000
12.500 1.2792 0.06711 0.05919 -0.0345 0.0154 1.0000
12.750 1.2801 0.07048 0.06279 -0.0340 0.0151 1.0000
13.000 1.2793 0.07417 0.06671 -0.0336 0.0149 1.0000
13.250 1.2757 0.07824 0.07101 -0.0336 0.0148 1.0000
13.500 1.2692 0.08268 0.07569 -0.0340 0.0147 1.0000
13.750 1.2603 0.08750 0.08076 -0.0349 0.0146 1.0000
14.000 1.2494 0.09272 0.08622 -0.0363 0.0146 1.0000
14.250 1.2366 0.09832 0.09207 -0.0382 0.0146 1.0000
14.500 1.2227 0.10439 0.09837 -0.0408 0.0147 1.0000
14.750 1.2080 0.11098 0.10519 -0.0440 0.0147 1.0000
15.000 1.1925 0.11813 0.11257 -0.0479 0.0148 1.0000
15.250 1.1762 0.12598 0.12064 -0.0525 0.0149 1.0000
15.500 1.1587 0.13471 0.12958 -0.0580 0.0150 1.0000
15.750 1.1398 0.14466 0.13973 -0.0646 0.0153 1.0000
16.000 1.1185 0.15646 0.15169 -0.0725 0.0156 1.0000
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Polar data table (+)
Polar graphs
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