GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 100,000 Max Cl/Cd: 55.83 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe122-il-100000.txt Download as CSV file: xf-goe122-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4186 0.10263 0.09788 -0.0038 1.0000 0.0585
-8.000 -0.4154 0.10002 0.09532 -0.0070 1.0000 0.0606
-7.750 -0.4139 0.09819 0.09357 -0.0142 1.0000 0.0619
-7.500 -0.4023 0.09576 0.09112 -0.0255 1.0000 0.0624
-7.250 -0.3969 0.08948 0.08494 -0.0202 1.0000 0.0637
-7.000 -0.3872 0.08562 0.08111 -0.0169 1.0000 0.0661
-6.750 -0.3763 0.08225 0.07774 -0.0186 1.0000 0.0691
-6.500 -0.3623 0.07888 0.07438 -0.0240 1.0000 0.0737
-6.250 -0.3395 0.07513 0.07048 -0.0369 1.0000 0.0769
-6.000 -0.3364 0.07111 0.06663 -0.0305 1.0000 0.0799
-5.750 -0.3234 0.06803 0.06356 -0.0313 1.0000 0.0846
-5.500 -0.2972 0.06472 0.05997 -0.0417 1.0000 0.0913
-5.250 -0.2937 0.06098 0.05643 -0.0376 1.0000 0.0936
-5.000 -0.2845 0.05843 0.05391 -0.0365 1.0000 0.0985
-4.750 -0.2662 0.05533 0.05058 -0.0406 1.0000 0.1069
-4.500 -0.2609 0.05281 0.04817 -0.0378 1.0000 0.1109
-4.250 -0.2440 0.05019 0.04534 -0.0399 1.0000 0.1221
-3.750 -0.2237 0.04578 0.04097 -0.0376 1.0000 0.1424
-3.500 -0.2095 0.04360 0.03872 -0.0377 1.0000 0.1562
-3.250 -0.1951 0.04164 0.03670 -0.0376 1.0000 0.1719
-2.000 0.0736 0.02504 0.01757 -0.0654 0.9598 0.1315
-1.750 0.1282 0.02320 0.01484 -0.0685 0.9511 0.1056
-1.500 0.1772 0.02092 0.01240 -0.0721 0.9425 0.1000
-1.250 0.2202 0.01960 0.01084 -0.0742 0.9300 0.0972
-1.000 0.2599 0.01865 0.00978 -0.0757 0.9161 0.1006
-0.750 0.2952 0.01780 0.00887 -0.0762 0.9009 0.1011
-0.500 0.3258 0.01711 0.00816 -0.0757 0.8843 0.1025
-0.250 0.3524 0.01661 0.00763 -0.0744 0.8661 0.1050
0.000 0.3767 0.01608 0.00713 -0.0729 0.8459 0.1103
0.250 0.4013 0.01572 0.00671 -0.0712 0.8266 0.1225
0.500 0.4264 0.01517 0.00634 -0.0697 0.8068 0.1696
0.750 0.4554 0.01308 0.00600 -0.0687 0.7857 1.0000
1.000 0.4798 0.01313 0.00574 -0.0671 0.7653 1.0000
1.250 0.5045 0.01325 0.00565 -0.0658 0.7421 1.0000
1.500 0.5294 0.01339 0.00555 -0.0645 0.7214 1.0000
1.750 0.5546 0.01360 0.00558 -0.0635 0.6987 1.0000
2.000 0.5799 0.01382 0.00560 -0.0625 0.6784 1.0000
2.250 0.6055 0.01409 0.00571 -0.0617 0.6583 1.0000
2.500 0.6313 0.01438 0.00588 -0.0610 0.6388 1.0000
2.750 0.6571 0.01468 0.00604 -0.0604 0.6211 1.0000
3.000 0.6832 0.01500 0.00625 -0.0598 0.6052 1.0000
3.250 0.7094 0.01533 0.00650 -0.0593 0.5900 1.0000
3.500 0.7355 0.01565 0.00679 -0.0589 0.5752 1.0000
3.750 0.7616 0.01596 0.00706 -0.0584 0.5606 1.0000
4.000 0.7877 0.01627 0.00735 -0.0580 0.5465 1.0000
4.250 0.8139 0.01662 0.00773 -0.0576 0.5336 1.0000
4.500 0.8402 0.01698 0.00812 -0.0572 0.5215 1.0000
4.750 0.8663 0.01734 0.00850 -0.0568 0.5093 1.0000
5.000 0.8919 0.01763 0.00880 -0.0563 0.4942 1.0000
5.250 0.9167 0.01783 0.00901 -0.0555 0.4755 1.0000
5.500 0.9414 0.01805 0.00915 -0.0547 0.4565 1.0000
5.750 0.9665 0.01841 0.00952 -0.0541 0.4406 1.0000
6.000 0.9912 0.01878 0.00999 -0.0535 0.4238 1.0000
6.250 1.0149 0.01904 0.01036 -0.0527 0.4024 1.0000
6.500 1.0386 0.01929 0.01060 -0.0519 0.3819 1.0000
6.750 1.0623 0.01955 0.01106 -0.0512 0.3614 1.0000
7.000 1.0854 0.01973 0.01135 -0.0503 0.3388 1.0000
7.250 1.1076 0.01984 0.01164 -0.0494 0.3056 1.0000
7.500 1.1282 0.02021 0.01195 -0.0483 0.2434 1.0000
7.750 1.1404 0.02214 0.01318 -0.0466 0.1486 1.0000
8.000 1.1540 0.02416 0.01476 -0.0451 0.0950 1.0000
8.250 1.1683 0.02589 0.01643 -0.0436 0.0830 1.0000
8.500 1.1804 0.02770 0.01829 -0.0417 0.0758 1.0000
8.750 1.1927 0.02941 0.02006 -0.0399 0.0700 1.0000
9.000 1.2025 0.03166 0.02219 -0.0377 0.0666 1.0000
9.250 1.2199 0.03333 0.02402 -0.0361 0.0636 1.0000
9.500 1.2371 0.03526 0.02602 -0.0348 0.0596 1.0000
9.750 1.2587 0.03779 0.02850 -0.0339 0.0569 1.0000
10.000 1.2875 0.04199 0.03271 -0.0338 0.0551 1.0000
10.250 1.3024 0.04418 0.03532 -0.0322 0.0539 1.0000
10.500 1.3143 0.04676 0.03832 -0.0305 0.0523 1.0000
10.750 1.3246 0.05004 0.04201 -0.0288 0.0518 1.0000
11.000 1.3300 0.05371 0.04610 -0.0269 0.0520 1.0000
11.250 1.3301 0.05762 0.05041 -0.0249 0.0524 1.0000
11.500 1.3255 0.06174 0.05489 -0.0229 0.0530 1.0000
11.750 1.3163 0.06591 0.05936 -0.0208 0.0536 1.0000
12.000 1.3036 0.07023 0.06392 -0.0190 0.0541 1.0000
12.250 1.2905 0.07517 0.06908 -0.0180 0.0547 1.0000
12.500 1.2817 0.08038 0.07450 -0.0176 0.0553 1.0000
12.750 1.2609 0.08360 0.07795 -0.0176 0.0557 1.0000
13.000 1.2304 0.08819 0.08286 -0.0200 0.0566 1.0000
13.250 1.1821 0.09682 0.09182 -0.0269 0.0575 1.0000
13.500 1.1382 0.10783 0.10303 -0.0356 0.0581 1.0000
13.750 1.0592 0.13108 0.12638 -0.0536 0.0612 1.0000
14.000 1.0243 0.14916 0.14439 -0.0635 0.0690 1.0000
14.250 1.0373 0.14948 0.14475 -0.0614 0.0674 1.0000
14.500 0.7522 0.16449 0.15979 -0.0544 0.1398 1.0000
14.750 0.7397 0.16734 0.16263 -0.0565 0.1390 1.0000
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Polar data table (+)
Polar graphs
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