GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 500,000 Max Cl/Cd: 114.84 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe124-il-500000.txt Download as CSV file: xf-goe124-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.4) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3177 0.10283 0.10063 -0.0224 1.0000 0.0205
-8.500 -0.3157 0.09994 0.09777 -0.0264 1.0000 0.0206
-8.250 -0.3114 0.09626 0.09413 -0.0285 1.0000 0.0206
-8.000 -0.2982 0.09246 0.09034 -0.0268 1.0000 0.0209
-7.750 -0.2902 0.08973 0.08764 -0.0272 1.0000 0.0211
-7.500 -0.2730 0.08637 0.08429 -0.0308 0.9845 0.0214
-7.250 -0.2530 0.08280 0.08070 -0.0356 0.9655 0.0219
-7.000 -0.2367 0.07947 0.07734 -0.0395 0.9440 0.0226
-6.750 -0.2232 0.07632 0.07413 -0.0426 0.9233 0.0234
-6.500 -0.1920 0.07155 0.06923 -0.0561 0.9021 0.0247
-6.250 -0.1635 0.06676 0.06431 -0.0647 0.8864 0.0249
-6.000 -0.1508 0.06242 0.05991 -0.0661 0.8732 0.0251
-5.750 -0.1364 0.05984 0.05727 -0.0661 0.8603 0.0254
-5.500 -0.1175 0.05725 0.05459 -0.0676 0.8474 0.0257
-5.250 -0.0944 0.05444 0.05171 -0.0705 0.8348 0.0263
-5.000 -0.0679 0.05140 0.04857 -0.0742 0.8229 0.0271
-4.750 -0.0207 0.04689 0.04380 -0.0833 0.8116 0.0298
-4.500 0.0211 0.04238 0.03897 -0.0896 0.8004 0.0301
-4.250 0.0439 0.03782 0.03431 -0.0923 0.7888 0.0307
-4.000 0.0678 0.03583 0.03223 -0.0934 0.7771 0.0311
-3.750 0.0944 0.03388 0.03016 -0.0949 0.7663 0.0317
-3.500 0.1235 0.03185 0.02799 -0.0966 0.7554 0.0328
-3.250 0.1568 0.02938 0.02530 -0.0987 0.7452 0.0349
-3.000 0.1991 0.02537 0.02060 -0.1018 0.7361 0.0373
-2.750 0.2260 0.02342 0.01862 -0.1029 0.7255 0.0380
-2.500 0.2543 0.02213 0.01724 -0.1037 0.7163 0.0389
-2.250 0.2839 0.02090 0.01585 -0.1046 0.7083 0.0403
-2.000 0.3152 0.01984 0.01456 -0.1052 0.7003 0.0433
-1.750 0.3483 0.01818 0.01245 -0.1061 0.6927 0.0464
-1.500 0.3773 0.01700 0.01124 -0.1068 0.6847 0.0477
-1.250 0.4066 0.01621 0.01032 -0.1073 0.6768 0.0499
-1.000 0.4365 0.01637 0.01031 -0.1072 0.6690 0.0548
-0.750 0.4670 0.01459 0.00834 -0.1082 0.6619 0.0589
-0.500 0.4963 0.01404 0.00773 -0.1085 0.6545 0.0628
0.500 0.6168 0.01155 0.00454 -0.1086 0.6247 0.0458
0.750 0.6459 0.01107 0.00404 -0.1087 0.6166 0.0444
1.000 0.6750 0.01068 0.00363 -0.1088 0.6090 0.0443
1.250 0.7039 0.01044 0.00337 -0.1089 0.6008 0.0446
1.500 0.7329 0.01027 0.00319 -0.1091 0.5926 0.0450
1.750 0.7620 0.00998 0.00288 -0.1094 0.5832 0.0471
2.000 0.7910 0.00983 0.00275 -0.1096 0.5723 0.0485
2.250 0.8198 0.00977 0.00268 -0.1097 0.5619 0.0504
2.500 0.8483 0.00977 0.00263 -0.1098 0.5508 0.0535
2.750 0.8767 0.00978 0.00259 -0.1098 0.5370 0.0585
3.000 0.8987 0.00807 0.00279 -0.1090 0.5235 1.0000
3.250 0.9267 0.00822 0.00283 -0.1090 0.5090 1.0000
3.500 0.9546 0.00839 0.00291 -0.1090 0.4940 1.0000
3.750 0.9822 0.00858 0.00302 -0.1089 0.4772 1.0000
4.000 1.0096 0.00880 0.00315 -0.1089 0.4590 1.0000
4.250 1.0370 0.00903 0.00330 -0.1089 0.4414 1.0000
4.500 1.0641 0.00928 0.00348 -0.1088 0.4237 1.0000
4.750 1.0910 0.00955 0.00367 -0.1087 0.4072 1.0000
5.000 1.1179 0.00982 0.00388 -0.1087 0.3933 1.0000
5.250 1.1448 0.01010 0.00412 -0.1086 0.3814 1.0000
5.500 1.1713 0.01039 0.00436 -0.1085 0.3700 1.0000
5.750 1.1981 0.01064 0.00459 -0.1084 0.3589 1.0000
6.000 1.2247 0.01090 0.00485 -0.1083 0.3492 1.0000
6.250 1.2508 0.01121 0.00513 -0.1081 0.3384 1.0000
6.750 1.3025 0.01185 0.00570 -0.1077 0.3097 1.0000
7.000 1.3282 0.01217 0.00600 -0.1075 0.2942 1.0000
7.250 1.3538 0.01249 0.00631 -0.1073 0.2748 1.0000
7.500 1.3770 0.01307 0.00670 -0.1068 0.2329 1.0000
7.750 1.3926 0.01458 0.00768 -0.1055 0.1521 1.0000
8.000 1.4139 0.01536 0.00837 -0.1048 0.1331 1.0000
8.250 1.4356 0.01602 0.00899 -0.1040 0.1208 1.0000
8.500 1.4569 0.01669 0.00962 -0.1033 0.1107 1.0000
8.750 1.4796 0.01716 0.01013 -0.1027 0.1027 1.0000
9.000 1.5013 0.01772 0.01070 -0.1019 0.0941 1.0000
9.250 1.5222 0.01832 0.01127 -0.1011 0.0826 1.0000
9.500 1.5399 0.01919 0.01200 -0.0999 0.0601 1.0000
9.750 1.5497 0.02071 0.01327 -0.0976 0.0323 1.0000
10.000 1.5622 0.02186 0.01441 -0.0956 0.0253 1.0000
10.250 1.5728 0.02304 0.01563 -0.0934 0.0223 1.0000
10.500 1.5834 0.02403 0.01670 -0.0910 0.0210 1.0000
10.750 1.5904 0.02511 0.01787 -0.0882 0.0199 1.0000
11.000 1.5957 0.02644 0.01929 -0.0856 0.0190 1.0000
11.250 1.5976 0.02817 0.02110 -0.0830 0.0182 1.0000
11.500 1.5947 0.03047 0.02352 -0.0804 0.0174 1.0000
11.750 1.6008 0.03215 0.02532 -0.0789 0.0170 1.0000
12.000 1.6051 0.03411 0.02739 -0.0775 0.0164 1.0000
12.250 1.6077 0.03633 0.02972 -0.0763 0.0159 1.0000
12.500 1.6087 0.03882 0.03231 -0.0752 0.0155 1.0000
12.750 1.6081 0.04157 0.03516 -0.0743 0.0151 1.0000
13.000 1.6059 0.04459 0.03828 -0.0736 0.0148 1.0000
13.250 1.6016 0.04793 0.04172 -0.0730 0.0145 1.0000
13.500 1.5942 0.05167 0.04556 -0.0724 0.0142 1.0000
13.750 1.5850 0.05569 0.04970 -0.0719 0.0140 1.0000
14.000 1.5725 0.06006 0.05418 -0.0712 0.0137 1.0000
14.250 1.5709 0.06332 0.05756 -0.0711 0.0136 1.0000
14.500 1.5689 0.06673 0.06109 -0.0710 0.0134 1.0000
14.750 1.5662 0.07028 0.06476 -0.0711 0.0132 1.0000
15.000 1.5631 0.07394 0.06853 -0.0712 0.0131 1.0000
15.250 1.5598 0.07770 0.07240 -0.0715 0.0128 1.0000
15.500 1.5564 0.08154 0.07635 -0.0719 0.0126 1.0000
15.750 1.5528 0.08546 0.08038 -0.0725 0.0124 1.0000
16.000 1.5487 0.08950 0.08453 -0.0731 0.0122 1.0000
16.250 1.5446 0.09365 0.08880 -0.0739 0.0120 1.0000
16.500 1.5403 0.09790 0.09314 -0.0750 0.0117 1.0000
16.750 1.5358 0.10216 0.09751 -0.0760 0.0115 1.0000
17.000 1.5313 0.10643 0.10186 -0.0771 0.0114 1.0000
17.250 1.5269 0.11069 0.10621 -0.0782 0.0112 1.0000
17.500 1.5224 0.11493 0.11054 -0.0793 0.0111 1.0000
17.750 1.5179 0.11911 0.11481 -0.0803 0.0109 1.0000
18.000 1.5122 0.12338 0.11918 -0.0813 0.0108 1.0000
18.250 1.5036 0.12816 0.12410 -0.0824 0.0106 1.0000
18.500 1.4943 0.13381 0.12991 -0.0850 0.0106 1.0000
18.750 1.4857 0.13974 0.13600 -0.0883 0.0105 1.0000
19.000 1.4767 0.14587 0.14229 -0.0918 0.0105 1.0000
19.250 1.4672 0.15220 0.14878 -0.0956 0.0105 1.0000
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Polar data table (+)
Polar graphs
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