GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 50,000 Max Cl/Cd: 17.32 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe239-il-50000.txt Download as CSV file: xf-goe239-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 239 (MVA H.31) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2594 0.12217 0.11520 -0.0338 1.0000 0.1817
-9.250 -0.2705 0.12217 0.11533 -0.0334 1.0000 0.1869
-9.000 -0.2965 0.12433 0.11767 -0.0324 1.0000 0.1883
-8.750 -0.2640 0.11621 0.10950 -0.0307 1.0000 0.1949
-8.500 -0.2698 0.11500 0.10839 -0.0291 1.0000 0.2004
-8.250 -0.2940 0.11637 0.10992 -0.0271 1.0000 0.2035
-8.000 -0.3263 0.11850 0.11223 -0.0239 1.0000 0.2044
-7.750 -0.2852 0.10979 0.10344 -0.0233 1.0000 0.2118
-7.500 -0.2981 0.10923 0.10300 -0.0208 1.0000 0.2173
-7.250 -0.3276 0.11057 0.10450 -0.0175 1.0000 0.2198
-7.000 -0.3594 0.11243 0.10655 -0.0168 1.0000 0.2209
-6.750 -0.3230 0.10469 0.09874 -0.0132 1.0000 0.2309
-6.500 -0.3455 0.10507 0.09927 -0.0114 1.0000 0.2358
-6.250 -0.3584 0.10376 0.09808 -0.0110 1.0000 0.2388
-6.000 -0.3479 0.10006 0.09440 -0.0074 1.0000 0.2460
-5.750 -0.3649 0.10023 0.09470 -0.0087 1.0000 0.2532
-5.500 -0.3652 0.09715 0.09170 -0.0069 1.0000 0.2569
-5.250 -0.3639 0.09483 0.08943 -0.0044 1.0000 0.2634
-5.000 -0.3735 0.09453 0.08924 -0.0093 1.0000 0.2716
-4.750 -0.3717 0.09130 0.08608 -0.0045 1.0000 0.2757
-4.500 -0.3716 0.09115 0.08597 -0.0112 1.0000 0.2877
-4.250 -0.3730 0.08781 0.08271 -0.0054 1.0000 0.2914
-4.000 -0.3480 0.08493 0.07980 -0.0114 0.9941 0.3069
-3.750 -0.3075 0.08106 0.07584 -0.0188 0.9826 0.3240
-3.500 -0.2665 0.07740 0.07209 -0.0267 0.9710 0.3404
-3.250 -0.2304 0.07403 0.06865 -0.0327 0.9592 0.3572
-3.000 -0.1998 0.07107 0.06563 -0.0364 0.9475 0.3771
-2.750 0.0123 0.05039 0.04300 -0.1024 0.9426 0.1855
-2.500 0.0725 0.04622 0.03820 -0.1121 0.9328 0.1853
-2.250 0.1366 0.04264 0.03378 -0.1213 0.9247 0.1894
-2.000 0.1851 0.04151 0.03237 -0.1260 0.9149 0.2027
-1.750 0.2219 0.04078 0.03149 -0.1286 0.9038 0.2158
-1.500 0.2712 0.04006 0.03058 -0.1328 0.8955 0.2427
-1.250 0.3032 0.04002 0.03049 -0.1342 0.8844 0.2752
-1.000 0.3352 0.04011 0.03064 -0.1352 0.8743 0.3258
-0.750 0.3765 0.03959 0.03019 -0.1374 0.8661 0.4198
-0.500 0.3986 0.03976 0.03039 -0.1369 0.8557 0.4781
-0.250 0.4415 0.03945 0.03008 -0.1391 0.8483 0.5369
0.000 0.4562 0.04011 0.03079 -0.1377 0.8372 0.5747
0.250 0.4893 0.04015 0.03089 -0.1385 0.8289 0.6256
0.500 0.5158 0.04047 0.03123 -0.1390 0.8191 0.6627
0.750 0.5406 0.04070 0.03162 -0.1391 0.8097 0.7057
1.000 0.5635 0.04013 0.03160 -0.1376 0.8010 1.0000
1.250 0.5880 0.04149 0.03261 -0.1391 0.7898 1.0000
1.500 0.6303 0.04208 0.03279 -0.1419 0.7812 1.0000
1.750 0.6528 0.04320 0.03368 -0.1419 0.7704 1.0000
2.000 0.6712 0.04451 0.03481 -0.1414 0.7597 1.0000
2.250 0.7182 0.04447 0.03456 -0.1436 0.7517 1.0000
2.500 0.7254 0.04626 0.03627 -0.1419 0.7394 1.0000
2.750 0.7437 0.04756 0.03749 -0.1412 0.7284 1.0000
3.000 0.7908 0.04725 0.03707 -0.1428 0.7202 1.0000
3.250 0.7970 0.04923 0.03901 -0.1411 0.7074 1.0000
3.500 0.8109 0.05083 0.04058 -0.1400 0.6957 1.0000
3.750 0.8641 0.04989 0.03959 -0.1416 0.6883 1.0000
4.000 0.8669 0.05225 0.04194 -0.1397 0.6749 1.0000
4.250 0.8729 0.05452 0.04422 -0.1381 0.6625 1.0000
4.500 0.8958 0.05565 0.04534 -0.1376 0.6520 1.0000
4.750 0.9284 0.05599 0.04570 -0.1375 0.6424 1.0000
5.000 0.9253 0.05918 0.04892 -0.1358 0.6295 1.0000
5.250 0.9356 0.06144 0.05120 -0.1347 0.6186 1.0000
5.500 0.9712 0.06163 0.05143 -0.1347 0.6101 1.0000
5.750 0.9546 0.06630 0.05613 -0.1329 0.5978 1.0000
6.000 0.9690 0.06843 0.05832 -0.1321 0.5885 1.0000
6.250 0.9795 0.07091 0.06084 -0.1314 0.5790 1.0000
6.500 0.9667 0.07568 0.06565 -0.1304 0.5706 1.0000
6.750 0.9742 0.07871 0.06874 -0.1300 0.5633 1.0000
7.000 0.9758 0.08234 0.07241 -0.1294 0.5565 1.0000
7.250 0.9591 0.08755 0.07767 -0.1290 0.5511 1.0000
7.500 0.9569 0.09184 0.08202 -0.1290 0.5485 1.0000
7.750 0.9402 0.09762 0.08786 -0.1295 0.5513 1.0000
8.000 0.9351 0.10261 0.09292 -0.1302 0.5554 1.0000
8.250 0.9507 0.10670 0.09712 -0.1315 0.5593 1.0000
8.500 0.8571 0.12048 0.11098 -0.1368 0.6554 1.0000
8.750 0.8633 0.12259 0.11315 -0.1360 0.6429 1.0000
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Polar data table (+)
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