GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 100,000 Max Cl/Cd: 59.52 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe101-il-100000-n5.txt Download as CSV file: xf-goe101-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3716 0.10638 0.10156 -0.0213 1.0000 0.0314
-8.250 -0.3689 0.10361 0.09885 -0.0228 1.0000 0.0315
-8.000 -0.3666 0.10080 0.09611 -0.0241 1.0000 0.0315
-7.750 -0.3619 0.09776 0.09313 -0.0261 1.0000 0.0316
-7.500 -0.3553 0.09447 0.08988 -0.0287 1.0000 0.0316
-7.250 -0.3477 0.09101 0.08645 -0.0313 1.0000 0.0317
-7.000 -0.3392 0.08749 0.08297 -0.0337 1.0000 0.0317
-6.750 -0.3320 0.08338 0.07892 -0.0350 1.0000 0.0318
-6.500 -0.3305 0.07885 0.07446 -0.0321 1.0000 0.0325
-6.250 -0.3246 0.07553 0.07115 -0.0314 1.0000 0.0332
-6.000 -0.3181 0.07256 0.06822 -0.0311 1.0000 0.0344
-5.750 -0.3099 0.06968 0.06537 -0.0319 1.0000 0.0364
-5.500 -0.2988 0.06665 0.06234 -0.0342 1.0000 0.0395
-5.250 -0.2692 0.06373 0.05915 -0.0428 1.0000 0.0428
-4.750 -0.2360 0.05453 0.04996 -0.0464 0.9925 0.0450
-4.500 -0.2033 0.05045 0.04578 -0.0508 0.9836 0.0480
-4.250 -0.1463 0.04507 0.03968 -0.0595 0.9738 0.0428
-4.000 -0.1131 0.04021 0.03466 -0.0632 0.9644 0.0420
-3.750 -0.0784 0.03575 0.02994 -0.0667 0.9546 0.0398
-3.500 -0.0405 0.03184 0.02557 -0.0697 0.9438 0.0394
-3.000 0.0340 0.02615 0.01862 -0.0732 0.9189 0.0433
-2.750 0.0655 0.02381 0.01613 -0.0748 0.9047 0.0470
-2.500 0.0990 0.02218 0.01410 -0.0757 0.8893 0.0498
-2.250 0.1322 0.02056 0.01206 -0.0763 0.8730 0.0503
-2.000 0.1644 0.01931 0.01045 -0.0766 0.8558 0.0516
-1.750 0.1948 0.01864 0.00941 -0.0765 0.8361 0.0555
-1.500 0.2242 0.01772 0.00826 -0.0763 0.8160 0.0556
-1.250 0.2529 0.01692 0.00728 -0.0760 0.7960 0.0556
-1.000 0.2804 0.01627 0.00650 -0.0755 0.7753 0.0557
-0.750 0.3074 0.01574 0.00583 -0.0750 0.7559 0.0560
-0.500 0.3338 0.01528 0.00528 -0.0744 0.7368 0.0567
-0.250 0.3602 0.01492 0.00480 -0.0738 0.7179 0.0581
0.000 0.3870 0.01471 0.00444 -0.0734 0.7001 0.0605
0.250 0.4136 0.01460 0.00417 -0.0729 0.6835 0.0642
0.750 0.4678 0.01438 0.00380 -0.0721 0.6534 0.0944
1.000 0.5007 0.01228 0.00375 -0.0732 0.6394 1.0000
1.250 0.5270 0.01248 0.00373 -0.0727 0.6263 1.0000
1.500 0.5534 0.01268 0.00377 -0.0723 0.6144 1.0000
1.750 0.5798 0.01289 0.00384 -0.0719 0.6039 1.0000
2.000 0.6062 0.01311 0.00394 -0.0716 0.5934 1.0000
2.250 0.6325 0.01334 0.00409 -0.0712 0.5833 1.0000
2.500 0.6589 0.01358 0.00426 -0.0709 0.5747 1.0000
2.750 0.6853 0.01382 0.00447 -0.0706 0.5659 1.0000
3.000 0.7116 0.01408 0.00469 -0.0703 0.5572 1.0000
3.250 0.7377 0.01433 0.00490 -0.0699 0.5483 1.0000
3.500 0.7636 0.01458 0.00519 -0.0695 0.5376 1.0000
3.750 0.7891 0.01483 0.00543 -0.0690 0.5258 1.0000
4.000 0.8142 0.01506 0.00565 -0.0684 0.5121 1.0000
4.250 0.8393 0.01530 0.00593 -0.0678 0.4987 1.0000
4.500 0.8647 0.01556 0.00622 -0.0673 0.4874 1.0000
4.750 0.8901 0.01583 0.00657 -0.0668 0.4767 1.0000
5.000 0.9156 0.01612 0.00697 -0.0664 0.4669 1.0000
5.250 0.9409 0.01641 0.00739 -0.0659 0.4573 1.0000
5.500 0.9658 0.01670 0.00779 -0.0654 0.4456 1.0000
5.750 0.9906 0.01698 0.00824 -0.0648 0.4325 1.0000
6.000 1.0150 0.01727 0.00869 -0.0641 0.4183 1.0000
6.250 1.0370 0.01748 0.00900 -0.0630 0.3869 1.0000
6.500 1.0582 0.01778 0.00933 -0.0619 0.3403 1.0000
6.750 1.0753 0.01856 0.00972 -0.0604 0.2562 1.0000
7.000 1.0895 0.02002 0.01072 -0.0588 0.1845 1.0000
7.250 1.1007 0.02198 0.01210 -0.0572 0.0923 1.0000
7.500 1.1110 0.02404 0.01373 -0.0552 0.0376 1.0000
7.750 1.1246 0.02563 0.01539 -0.0533 0.0287 1.0000
8.000 1.1386 0.02708 0.01702 -0.0516 0.0246 1.0000
8.250 1.1494 0.02878 0.01891 -0.0496 0.0226 1.0000
8.500 1.1581 0.03057 0.02089 -0.0473 0.0215 1.0000
8.750 1.1682 0.03213 0.02267 -0.0452 0.0205 1.0000
9.000 1.1769 0.03377 0.02451 -0.0431 0.0191 1.0000
9.250 1.1839 0.03550 0.02640 -0.0408 0.0179 1.0000
9.500 1.1895 0.03741 0.02847 -0.0383 0.0172 1.0000
9.750 1.1966 0.03949 0.03070 -0.0362 0.0167 1.0000
10.000 1.2056 0.04169 0.03307 -0.0344 0.0162 1.0000
10.250 1.2153 0.04412 0.03577 -0.0328 0.0158 1.0000
10.500 1.2242 0.04676 0.03863 -0.0312 0.0155 1.0000
10.750 1.2299 0.04954 0.04165 -0.0298 0.0150 1.0000
11.000 1.2310 0.05243 0.04477 -0.0285 0.0144 1.0000
11.250 1.2290 0.05561 0.04817 -0.0274 0.0139 1.0000
11.500 1.2247 0.05916 0.05195 -0.0267 0.0135 1.0000
11.750 1.2182 0.06306 0.05609 -0.0265 0.0133 1.0000
12.000 1.2079 0.06757 0.06084 -0.0268 0.0130 1.0000
12.250 1.1968 0.07227 0.06579 -0.0277 0.0128 1.0000
12.500 1.1847 0.07725 0.07102 -0.0292 0.0128 1.0000
12.750 1.1716 0.08259 0.07659 -0.0313 0.0128 1.0000
13.000 1.1573 0.08843 0.08266 -0.0341 0.0128 1.0000
13.250 1.1435 0.09447 0.08891 -0.0373 0.0129 1.0000
13.500 1.1279 0.10123 0.09586 -0.0412 0.0129 1.0000
13.750 1.1124 0.10839 0.10321 -0.0457 0.0130 1.0000
14.000 1.0965 0.11627 0.11128 -0.0508 0.0132 1.0000
14.250 1.0784 0.12565 0.12084 -0.0570 0.0136 1.0000
14.500 1.0540 0.13859 0.13398 -0.0654 0.0144 1.0000
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Polar data table (+)
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