GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 500,000 Max Cl/Cd: 72.44 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe310-il-500000-n5.txt Download as CSV file: xf-goe310-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 310 (MVA H.42) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3522 0.10921 0.10686 -0.0320 1.0000 0.0075
-10.250 -0.3513 0.10579 0.10346 -0.0327 1.0000 0.0075
-10.000 -0.3549 0.10132 0.09903 -0.0337 1.0000 0.0081
-9.750 -0.3464 0.10042 0.09814 -0.0335 1.0000 0.0086
-9.500 -0.3518 0.09612 0.09387 -0.0341 1.0000 0.0084
-9.250 -0.3541 0.09312 0.09091 -0.0341 1.0000 0.0084
-9.000 -0.3419 0.09017 0.08797 -0.0369 0.9984 0.0088
-8.750 -0.3337 0.08558 0.08339 -0.0410 0.9924 0.0089
-8.250 -0.3197 0.07596 0.07379 -0.0507 0.9761 0.0095
-7.250 -0.2985 0.02601 0.02261 -0.0939 0.9257 0.0125
-7.000 -0.2867 0.02124 0.01711 -0.0932 0.9166 0.0138
-6.750 -0.2695 0.01862 0.01397 -0.0919 0.9083 0.0149
-6.500 -0.2428 0.01844 0.01371 -0.0919 0.9018 0.0153
-6.250 -0.2171 0.01825 0.01345 -0.0916 0.8941 0.0160
-6.000 -0.1928 0.01762 0.01264 -0.0911 0.8863 0.0170
-5.750 -0.1698 0.01665 0.01137 -0.0902 0.8774 0.0183
-5.500 -0.1456 0.01605 0.01046 -0.0893 0.8687 0.0193
-5.250 -0.1223 0.01515 0.00945 -0.0886 0.8597 0.0201
-5.000 -0.0980 0.01473 0.00894 -0.0880 0.8490 0.0209
-4.750 -0.0735 0.01424 0.00834 -0.0873 0.8370 0.0217
-4.500 -0.0490 0.01373 0.00768 -0.0865 0.8232 0.0225
-4.250 -0.0241 0.01332 0.00712 -0.0858 0.8078 0.0236
-4.000 0.0008 0.01300 0.00663 -0.0850 0.7905 0.0244
-3.750 0.0254 0.01268 0.00613 -0.0842 0.7714 0.0249
-3.500 0.0500 0.01243 0.00572 -0.0834 0.7512 0.0253
-3.250 0.0734 0.01183 0.00496 -0.0824 0.7319 0.0262
-3.000 0.0970 0.01130 0.00433 -0.0815 0.7147 0.0270
-2.750 0.1212 0.01099 0.00392 -0.0807 0.6998 0.0275
-2.500 0.1458 0.01073 0.00358 -0.0799 0.6859 0.0281
-2.250 0.1705 0.01051 0.00328 -0.0792 0.6730 0.0285
-2.000 0.1954 0.01033 0.00302 -0.0785 0.6611 0.0290
-1.500 0.2458 0.01002 0.00259 -0.0773 0.6405 0.0297
-1.250 0.2711 0.00990 0.00241 -0.0767 0.6313 0.0305
-1.000 0.2965 0.00981 0.00226 -0.0761 0.6223 0.0312
-0.750 0.3222 0.00972 0.00213 -0.0756 0.6144 0.0314
-0.500 0.3472 0.00967 0.00200 -0.0749 0.6044 0.0317
-0.250 0.3721 0.00965 0.00189 -0.0742 0.5906 0.0322
0.000 0.3976 0.00961 0.00181 -0.0737 0.5809 0.0327
0.250 0.4228 0.00960 0.00174 -0.0731 0.5725 0.0332
0.500 0.4481 0.00959 0.00168 -0.0725 0.5623 0.0346
0.750 0.4731 0.00960 0.00164 -0.0718 0.5506 0.0362
1.000 0.4982 0.00962 0.00163 -0.0712 0.5412 0.0386
1.250 0.5233 0.00962 0.00162 -0.0706 0.5315 0.0420
1.500 0.5458 0.00940 0.00167 -0.0696 0.5200 0.1429
1.750 0.5697 0.00945 0.00175 -0.0688 0.5035 0.1743
2.000 0.5930 0.00957 0.00181 -0.0678 0.4805 0.1871
2.250 0.6167 0.00969 0.00187 -0.0670 0.4586 0.1974
2.500 0.6402 0.00982 0.00195 -0.0661 0.4374 0.2091
2.750 0.6610 0.01010 0.00206 -0.0648 0.3914 0.2167
3.000 0.6779 0.01070 0.00231 -0.0629 0.3151 0.2233
3.250 0.6944 0.01136 0.00264 -0.0609 0.2407 0.2315
3.500 0.7132 0.01185 0.00294 -0.0594 0.1912 0.2433
3.750 0.7324 0.01221 0.00323 -0.0579 0.1545 0.2812
4.000 0.7504 0.01240 0.00355 -0.0562 0.1231 0.4007
4.250 0.7483 0.01196 0.00383 -0.0503 0.0661 0.8104
4.750 0.9211 0.01286 0.00503 -0.0772 0.0541 0.9994
5.000 0.9459 0.01311 0.00530 -0.0768 0.0532 1.0000
5.250 0.9664 0.01336 0.00557 -0.0754 0.0525 1.0000
5.500 0.9866 0.01362 0.00587 -0.0739 0.0517 1.0000
5.750 1.0063 0.01391 0.00620 -0.0724 0.0510 1.0000
6.000 1.0251 0.01426 0.00658 -0.0708 0.0495 1.0000
6.250 1.0423 0.01469 0.00706 -0.0688 0.0472 1.0000
6.500 1.0617 0.01497 0.00736 -0.0673 0.0460 1.0000
6.750 1.0811 0.01524 0.00768 -0.0658 0.0448 1.0000
7.000 1.0997 0.01555 0.00803 -0.0641 0.0435 1.0000
7.250 1.1178 0.01587 0.00839 -0.0624 0.0418 1.0000
7.500 1.1353 0.01622 0.00876 -0.0606 0.0397 1.0000
7.750 1.1525 0.01657 0.00913 -0.0587 0.0373 1.0000
8.000 1.1722 0.01677 0.00939 -0.0573 0.0345 1.0000
8.250 1.1906 0.01703 0.00964 -0.0557 0.0299 1.0000
8.500 1.2046 0.01745 0.00993 -0.0534 0.0173 1.0000
8.750 1.2149 0.01796 0.01046 -0.0503 0.0150 1.0000
9.000 1.2235 0.01858 0.01110 -0.0470 0.0128 1.0000
9.250 1.2339 0.01918 0.01177 -0.0441 0.0117 1.0000
9.500 1.2449 0.01978 0.01245 -0.0415 0.0109 1.0000
9.750 1.2555 0.02046 0.01320 -0.0389 0.0103 1.0000
10.000 1.2650 0.02123 0.01404 -0.0363 0.0094 1.0000
10.250 1.2722 0.02219 0.01506 -0.0335 0.0085 1.0000
10.500 1.2794 0.02320 0.01616 -0.0309 0.0081 1.0000
10.750 1.2883 0.02414 0.01719 -0.0287 0.0079 1.0000
11.000 1.2964 0.02519 0.01833 -0.0266 0.0075 1.0000
11.250 1.3030 0.02640 0.01964 -0.0244 0.0073 1.0000
11.500 1.3096 0.02766 0.02099 -0.0224 0.0070 1.0000
11.750 1.3152 0.02906 0.02249 -0.0205 0.0067 1.0000
12.000 1.3198 0.03061 0.02413 -0.0188 0.0066 1.0000
12.250 1.3230 0.03237 0.02597 -0.0171 0.0063 1.0000
12.500 1.3263 0.03420 0.02790 -0.0157 0.0062 1.0000
12.750 1.3262 0.03645 0.03023 -0.0144 0.0058 1.0000
13.000 1.3265 0.03876 0.03265 -0.0133 0.0058 1.0000
13.250 1.3239 0.04149 0.03549 -0.0124 0.0056 1.0000
13.500 1.3228 0.04413 0.03824 -0.0117 0.0056 1.0000
13.750 1.3282 0.04616 0.04040 -0.0112 0.0053 1.0000
14.000 1.3269 0.04899 0.04335 -0.0108 0.0052 1.0000
14.250 1.3287 0.05154 0.04600 -0.0106 0.0050 1.0000
14.500 1.3275 0.05450 0.04908 -0.0105 0.0048 1.0000
14.750 1.3227 0.05797 0.05268 -0.0104 0.0049 1.0000
15.000 1.3215 0.06109 0.05591 -0.0106 0.0047 1.0000
15.250 1.3168 0.06471 0.05966 -0.0109 0.0047 1.0000
15.500 1.3138 0.06823 0.06329 -0.0114 0.0046 1.0000
15.750 1.3080 0.07219 0.06738 -0.0119 0.0045 1.0000
16.000 1.3031 0.07611 0.07142 -0.0127 0.0045 1.0000
16.250 1.2977 0.08027 0.07570 -0.0137 0.0043 1.0000
16.500 1.2920 0.08454 0.08009 -0.0149 0.0043 1.0000
16.750 1.2848 0.08911 0.08478 -0.0161 0.0043 1.0000
17.000 1.2780 0.09379 0.08957 -0.0177 0.0042 1.0000
17.250 1.2696 0.09880 0.09470 -0.0194 0.0041 1.0000
17.500 1.2605 0.10406 0.10009 -0.0213 0.0041 1.0000
17.750 1.2502 0.10959 0.10576 -0.0234 0.0041 1.0000
18.000 1.2421 0.11492 0.11117 -0.0257 0.0040 1.0000
18.250 1.2303 0.12099 0.11739 -0.0283 0.0040 1.0000
18.500 1.2200 0.12696 0.12348 -0.0310 0.0040 1.0000
18.750 1.2089 0.13323 0.12988 -0.0340 0.0040 1.0000
19.000 1.1981 0.13954 0.13629 -0.0371 0.0040 1.0000
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