GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 500,000 Max Cl/Cd: 95.7 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe122-il-500000.txt Download as CSV file: xf-goe122-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4306 0.09743 0.09528 0.0004 1.0000 0.0168
-8.000 -0.4245 0.09396 0.09183 -0.0019 1.0000 0.0174
-7.750 -0.4195 0.09039 0.08829 -0.0061 1.0000 0.0179
-7.500 -0.4104 0.08615 0.08407 -0.0130 1.0000 0.0181
-7.250 -0.3954 0.08134 0.07927 -0.0199 1.0000 0.0182
-7.000 -0.3785 0.07648 0.07439 -0.0260 1.0000 0.0182
-6.750 -0.3661 0.07077 0.06867 -0.0305 1.0000 0.0184
-6.500 -0.3567 0.06758 0.06549 -0.0304 1.0000 0.0187
-6.250 -0.3427 0.06465 0.06256 -0.0317 1.0000 0.0190
-6.000 -0.3275 0.06149 0.05940 -0.0339 1.0000 0.0195
-5.750 -0.2997 0.05756 0.05541 -0.0392 0.9933 0.0205
-5.500 -0.2486 0.05107 0.04869 -0.0502 0.9810 0.0230
-5.250 -0.2085 0.04518 0.04252 -0.0565 0.9685 0.0233
-4.250 -0.1164 0.03165 0.02838 -0.0618 0.9132 0.0268
-4.000 -0.0829 0.02981 0.02600 -0.0613 0.9012 0.0299
-3.750 -0.0615 0.02430 0.02014 -0.0621 0.8899 0.0312
-3.500 -0.0378 0.02282 0.01858 -0.0620 0.8778 0.0323
-3.250 -0.0125 0.02147 0.01705 -0.0617 0.8655 0.0341
-3.000 0.0173 0.02225 0.01748 -0.0606 0.8524 0.0387
-2.750 0.0411 0.01816 0.01315 -0.0611 0.8397 0.0417
-2.500 0.0676 0.01725 0.01209 -0.0609 0.8251 0.0449
-1.250 0.2064 0.01208 0.00570 -0.0587 0.7343 0.0473
-1.000 0.2341 0.01112 0.00454 -0.0583 0.7124 0.0445
-0.750 0.2615 0.01046 0.00369 -0.0578 0.6908 0.0424
-0.500 0.2890 0.01004 0.00316 -0.0575 0.6701 0.0418
-0.250 0.3164 0.00975 0.00276 -0.0572 0.6503 0.0419
0.000 0.3439 0.00953 0.00245 -0.0570 0.6312 0.0422
0.250 0.3716 0.00937 0.00221 -0.0569 0.6120 0.0429
0.500 0.3993 0.00926 0.00203 -0.0568 0.5916 0.0445
0.750 0.4271 0.00919 0.00187 -0.0567 0.5704 0.0453
1.000 0.4549 0.00916 0.00174 -0.0566 0.5472 0.0465
1.250 0.4826 0.00918 0.00165 -0.0565 0.5230 0.0483
1.500 0.5102 0.00925 0.00160 -0.0564 0.4989 0.0515
1.750 0.5379 0.00927 0.00162 -0.0563 0.4787 0.0782
2.000 0.5629 0.00726 0.00178 -0.0562 0.4634 1.0000
2.250 0.5904 0.00744 0.00184 -0.0561 0.4498 1.0000
2.500 0.6178 0.00763 0.00192 -0.0560 0.4354 1.0000
2.750 0.6451 0.00782 0.00201 -0.0559 0.4213 1.0000
3.000 0.6725 0.00800 0.00211 -0.0559 0.4097 1.0000
3.250 0.7000 0.00815 0.00221 -0.0558 0.3996 1.0000
3.500 0.7275 0.00830 0.00234 -0.0557 0.3901 1.0000
3.750 0.7548 0.00848 0.00247 -0.0557 0.3802 1.0000
4.000 0.7821 0.00866 0.00259 -0.0556 0.3669 1.0000
4.250 0.8096 0.00880 0.00273 -0.0555 0.3550 1.0000
4.500 0.8369 0.00896 0.00287 -0.0555 0.3434 1.0000
4.750 0.8641 0.00913 0.00302 -0.0554 0.3301 1.0000
5.000 0.8911 0.00934 0.00319 -0.0553 0.3138 1.0000
5.250 0.9178 0.00959 0.00338 -0.0552 0.2923 1.0000
5.500 0.9434 0.01002 0.00362 -0.0551 0.2467 1.0000
5.750 0.9666 0.01089 0.00410 -0.0547 0.1796 1.0000
6.000 0.9911 0.01152 0.00458 -0.0544 0.1487 1.0000
6.250 1.0110 0.01297 0.00547 -0.0538 0.0527 1.0000
6.500 1.0357 0.01355 0.00605 -0.0533 0.0438 1.0000
6.750 1.0609 0.01401 0.00658 -0.0530 0.0411 1.0000
7.000 1.0852 0.01460 0.00723 -0.0526 0.0381 1.0000
7.250 1.1078 0.01544 0.00817 -0.0520 0.0348 1.0000
7.500 1.1307 0.01617 0.00899 -0.0514 0.0327 1.0000
7.750 1.1541 0.01678 0.00969 -0.0508 0.0308 1.0000
8.000 1.1761 0.01755 0.01052 -0.0502 0.0287 1.0000
8.250 1.1958 0.01859 0.01162 -0.0493 0.0264 1.0000
8.500 1.2107 0.02020 0.01335 -0.0478 0.0244 1.0000
8.750 1.2330 0.02077 0.01400 -0.0471 0.0231 1.0000
9.000 1.2531 0.02159 0.01490 -0.0462 0.0216 1.0000
9.250 1.2723 0.02245 0.01581 -0.0453 0.0203 1.0000
9.500 1.2887 0.02358 0.01697 -0.0441 0.0191 1.0000
9.750 1.2981 0.02562 0.01910 -0.0421 0.0180 1.0000
10.000 1.3171 0.02629 0.01989 -0.0411 0.0171 1.0000
10.250 1.3325 0.02739 0.02108 -0.0397 0.0163 1.0000
10.500 1.3466 0.02851 0.02230 -0.0383 0.0155 1.0000
10.750 1.3584 0.02961 0.02349 -0.0366 0.0149 1.0000
11.000 1.3671 0.03081 0.02475 -0.0347 0.0144 1.0000
11.250 1.3729 0.03248 0.02648 -0.0326 0.0140 1.0000
11.500 1.3741 0.03563 0.02976 -0.0303 0.0134 1.0000
11.750 1.3805 0.03705 0.03134 -0.0288 0.0131 1.0000
12.000 1.3858 0.03880 0.03326 -0.0275 0.0126 1.0000
12.250 1.3894 0.04094 0.03556 -0.0263 0.0122 1.0000
12.500 1.3914 0.04338 0.03815 -0.0252 0.0118 1.0000
12.750 1.3919 0.04602 0.04096 -0.0245 0.0116 1.0000
13.000 1.3914 0.04883 0.04392 -0.0240 0.0113 1.0000
13.250 1.3893 0.05191 0.04716 -0.0239 0.0111 1.0000
13.500 1.3855 0.05532 0.05072 -0.0242 0.0109 1.0000
13.750 1.3807 0.05896 0.05450 -0.0249 0.0108 1.0000
14.000 1.3740 0.06302 0.05872 -0.0258 0.0106 1.0000
14.250 1.3661 0.06736 0.06319 -0.0272 0.0105 1.0000
14.500 1.3561 0.07219 0.06818 -0.0288 0.0104 1.0000
14.750 1.3441 0.07743 0.07358 -0.0307 0.0104 1.0000
15.000 1.3301 0.08323 0.07954 -0.0331 0.0103 1.0000
15.250 1.3142 0.08966 0.08615 -0.0360 0.0103 1.0000
15.500 1.2964 0.09678 0.09344 -0.0395 0.0103 1.0000
15.750 1.2776 0.10443 0.10127 -0.0434 0.0103 1.0000
16.000 1.2542 0.11339 0.11044 -0.0483 0.0104 1.0000
16.250 1.2106 0.12777 0.12515 -0.0564 0.0107 1.0000
16.500 1.1242 0.15682 0.15461 -0.0745 0.0119 1.0000
16.750 1.0800 0.17793 0.17581 -0.0867 0.0127 1.0000
17.000 1.0636 0.18954 0.18739 -0.0926 0.0133 1.0000
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Polar data table (+)
Polar graphs
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