GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.26 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe122-il-1000000-n5.txt Download as CSV file: xf-goe122-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4308 0.09040 0.08890 -0.0053 0.9807 0.0048
-8.000 -0.4265 0.08603 0.08443 -0.0084 0.9232 0.0049
-7.750 -0.4232 0.08109 0.07942 -0.0127 0.9031 0.0051
-7.500 -0.4150 0.07411 0.07239 -0.0206 0.8894 0.0055
-7.000 -0.3807 0.06612 0.06427 -0.0305 0.8656 0.0058
-6.750 -0.3603 0.06155 0.05962 -0.0360 0.8545 0.0060
-6.500 -0.3376 0.05585 0.05381 -0.0425 0.8436 0.0064
-6.000 -0.2902 0.01537 0.01111 -0.0646 0.8301 0.0109
-5.750 -0.2624 0.01601 0.01178 -0.0645 0.8141 0.0113
-5.500 -0.2351 0.01605 0.01177 -0.0643 0.7967 0.0117
-5.000 -0.1828 0.01252 0.00752 -0.0642 0.7620 0.0143
-4.750 -0.1549 0.01280 0.00775 -0.0641 0.7420 0.0147
-4.500 -0.1272 0.01304 0.00793 -0.0640 0.7194 0.0152
-4.250 -0.0996 0.01289 0.00764 -0.0639 0.6985 0.0160
-4.000 -0.0721 0.01189 0.00634 -0.0638 0.6803 0.0177
-3.750 -0.0442 0.01167 0.00595 -0.0638 0.6640 0.0184
-3.500 -0.0166 0.01118 0.00532 -0.0638 0.6484 0.0190
-3.250 0.0114 0.01102 0.00508 -0.0638 0.6336 0.0194
-3.000 0.0394 0.01095 0.00495 -0.0638 0.6208 0.0199
-2.750 0.0674 0.01078 0.00470 -0.0638 0.6093 0.0206
-2.500 0.0954 0.01050 0.00432 -0.0638 0.5961 0.0212
-2.250 0.1234 0.01023 0.00394 -0.0638 0.5794 0.0219
-2.000 0.1514 0.01008 0.00368 -0.0638 0.5596 0.0227
-1.750 0.1794 0.00987 0.00337 -0.0638 0.5397 0.0232
-1.500 0.2073 0.00970 0.00309 -0.0637 0.5194 0.0235
-1.000 0.2629 0.00948 0.00261 -0.0637 0.4658 0.0240
-0.750 0.2907 0.00941 0.00243 -0.0637 0.4427 0.0241
-0.500 0.3187 0.00935 0.00229 -0.0637 0.4258 0.0243
-0.250 0.3466 0.00913 0.00200 -0.0638 0.4143 0.0247
0.000 0.3747 0.00894 0.00176 -0.0638 0.4048 0.0250
0.250 0.4029 0.00879 0.00157 -0.0639 0.3973 0.0256
0.500 0.4310 0.00872 0.00146 -0.0639 0.3896 0.0264
0.750 0.4593 0.00867 0.00140 -0.0639 0.3832 0.0272
1.000 0.4875 0.00865 0.00136 -0.0640 0.3761 0.0279
1.250 0.5156 0.00865 0.00133 -0.0640 0.3692 0.0287
1.500 0.5436 0.00869 0.00133 -0.0641 0.3574 0.0293
1.750 0.5714 0.00878 0.00134 -0.0641 0.3388 0.0297
2.000 0.5993 0.00884 0.00135 -0.0641 0.3268 0.0302
2.250 0.6273 0.00889 0.00138 -0.0642 0.3183 0.0309
2.500 0.6553 0.00896 0.00143 -0.0642 0.3100 0.0316
2.750 0.6831 0.00904 0.00148 -0.0642 0.3002 0.0321
3.000 0.7108 0.00914 0.00154 -0.0642 0.2870 0.0335
3.250 0.7378 0.00937 0.00167 -0.0642 0.2580 0.0413
3.750 0.7863 0.00831 0.00229 -0.0638 0.1764 1.0000
4.000 0.8133 0.00856 0.00247 -0.0637 0.1635 1.0000
4.250 0.8405 0.00877 0.00264 -0.0637 0.1546 1.0000
4.500 0.8676 0.00900 0.00282 -0.0636 0.1460 1.0000
4.750 0.8948 0.00920 0.00299 -0.0636 0.1375 1.0000
5.000 0.9213 0.00950 0.00321 -0.0635 0.1206 1.0000
5.250 0.9440 0.01055 0.00385 -0.0630 0.0407 1.0000
5.500 0.9705 0.01083 0.00411 -0.0629 0.0349 1.0000
5.750 0.9972 0.01106 0.00437 -0.0628 0.0327 1.0000
6.000 1.0238 0.01130 0.00463 -0.0627 0.0318 1.0000
6.250 1.0502 0.01155 0.00490 -0.0626 0.0308 1.0000
6.500 1.0764 0.01184 0.00520 -0.0624 0.0293 1.0000
6.750 1.1024 0.01214 0.00552 -0.0623 0.0277 1.0000
7.000 1.1281 0.01247 0.00587 -0.0621 0.0260 1.0000
7.250 1.1535 0.01284 0.00628 -0.0618 0.0243 1.0000
7.500 1.1790 0.01318 0.00666 -0.0616 0.0232 1.0000
7.750 1.2049 0.01341 0.00691 -0.0615 0.0226 1.0000
8.000 1.2305 0.01368 0.00721 -0.0613 0.0213 1.0000
8.250 1.2558 0.01399 0.00753 -0.0611 0.0189 1.0000
8.500 1.2802 0.01441 0.00792 -0.0608 0.0153 1.0000
8.750 1.3042 0.01485 0.00833 -0.0605 0.0123 1.0000
9.000 1.3280 0.01532 0.00882 -0.0601 0.0103 1.0000
9.250 1.3513 0.01582 0.00935 -0.0596 0.0089 1.0000
9.500 1.3739 0.01638 0.00994 -0.0591 0.0077 1.0000
9.750 1.3967 0.01689 0.01051 -0.0586 0.0071 1.0000
10.000 1.4188 0.01745 0.01111 -0.0580 0.0064 1.0000
10.250 1.4398 0.01810 0.01181 -0.0573 0.0057 1.0000
10.500 1.4603 0.01878 0.01255 -0.0566 0.0053 1.0000
10.750 1.4808 0.01941 0.01325 -0.0558 0.0050 1.0000
11.000 1.5003 0.02009 0.01400 -0.0549 0.0047 1.0000
11.250 1.5188 0.02082 0.01480 -0.0540 0.0044 1.0000
11.500 1.5361 0.02162 0.01567 -0.0528 0.0041 1.0000
11.750 1.5514 0.02253 0.01665 -0.0515 0.0039 1.0000
12.000 1.5631 0.02365 0.01787 -0.0498 0.0036 1.0000
12.250 1.5740 0.02460 0.01891 -0.0478 0.0036 1.0000
12.500 1.5819 0.02563 0.02003 -0.0456 0.0035 1.0000
12.750 1.5885 0.02685 0.02136 -0.0435 0.0034 1.0000
13.000 1.5941 0.02827 0.02288 -0.0418 0.0033 1.0000
13.250 1.5991 0.02988 0.02458 -0.0404 0.0032 1.0000
13.500 1.6031 0.03171 0.02653 -0.0392 0.0031 1.0000
13.750 1.6062 0.03376 0.02868 -0.0383 0.0030 1.0000
14.000 1.6083 0.03608 0.03111 -0.0378 0.0029 1.0000
14.250 1.6094 0.03866 0.03379 -0.0376 0.0028 1.0000
14.500 1.6088 0.04162 0.03686 -0.0377 0.0027 1.0000
14.750 1.6060 0.04501 0.04036 -0.0381 0.0026 1.0000
15.000 1.6009 0.04885 0.04432 -0.0389 0.0026 1.0000
15.250 1.5940 0.05307 0.04866 -0.0399 0.0025 1.0000
15.500 1.5841 0.05778 0.05350 -0.0411 0.0025 1.0000
15.750 1.5726 0.06286 0.05871 -0.0426 0.0025 1.0000
16.000 1.5594 0.06828 0.06425 -0.0443 0.0024 1.0000
16.250 1.5444 0.07419 0.07030 -0.0463 0.0024 1.0000
16.500 1.5290 0.08027 0.07650 -0.0485 0.0024 1.0000
16.750 1.5126 0.08659 0.08295 -0.0508 0.0024 1.0000
17.000 1.4954 0.09318 0.08966 -0.0532 0.0024 1.0000
17.250 1.4781 0.09986 0.09646 -0.0558 0.0023 1.0000
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Polar data table (+)
Polar graphs
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