GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 50,000 Max Cl/Cd: 37.26 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe116-il-50000-n5.txt Download as CSV file: xf-goe116-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 116 (MVA MK.3) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3784 0.10472 0.09822 -0.0356 1.0000 0.0373
-9.000 -0.3768 0.10073 0.09431 -0.0372 1.0000 0.0365
-8.750 -0.3766 0.09662 0.09030 -0.0391 1.0000 0.0356
-8.500 -0.3785 0.09235 0.08615 -0.0411 1.0000 0.0348
-8.250 -0.3838 0.08787 0.08181 -0.0432 1.0000 0.0340
-8.000 -0.3966 0.08242 0.07653 -0.0463 1.0000 0.0329
-7.750 -0.4004 0.07890 0.07314 -0.0475 1.0000 0.0326
-7.500 -0.4069 0.07551 0.06990 -0.0484 1.0000 0.0324
-7.250 -0.4164 0.07234 0.06685 -0.0487 1.0000 0.0322
-7.000 -0.4279 0.06931 0.06391 -0.0484 1.0000 0.0319
-6.750 -0.4244 0.06354 0.05810 -0.0535 0.9952 0.0315
-6.500 -0.3991 0.05324 0.04740 -0.0658 0.9835 0.0308
-6.250 -0.3698 0.04475 0.03816 -0.0754 0.9736 0.0304
-6.000 -0.3357 0.03904 0.03163 -0.0815 0.9659 0.0305
-5.750 -0.3033 0.03545 0.02737 -0.0847 0.9572 0.0310
-5.500 -0.2681 0.03280 0.02411 -0.0876 0.9499 0.0325
-5.250 -0.2337 0.03058 0.02155 -0.0904 0.9425 0.0361
-5.000 -0.1981 0.02883 0.01938 -0.0927 0.9355 0.0400
-4.750 -0.1621 0.02715 0.01742 -0.0950 0.9286 0.0450
-4.500 -0.1273 0.02566 0.01604 -0.0969 0.9214 0.0650
-4.250 -0.0909 0.02757 0.01773 -0.0984 0.9133 0.1646
-4.000 -0.0615 0.02823 0.01794 -0.0990 0.9046 0.1911
-3.750 -0.0274 0.02809 0.01747 -0.1004 0.8986 0.2064
-3.500 -0.0011 0.02827 0.01750 -0.1006 0.8900 0.2299
-3.250 0.0325 0.02771 0.01665 -0.1020 0.8845 0.2384
-3.000 0.0606 0.02726 0.01583 -0.1024 0.8765 0.2422
-2.750 0.0944 0.02672 0.01490 -0.1037 0.8710 0.2449
-2.500 0.1218 0.02640 0.01430 -0.1039 0.8632 0.2472
-2.250 0.1531 0.02598 0.01369 -0.1047 0.8577 0.2508
-2.000 0.1797 0.02580 0.01334 -0.1047 0.8502 0.2554
-1.750 0.2109 0.02557 0.01286 -0.1054 0.8446 0.2599
-1.500 0.2382 0.02544 0.01261 -0.1055 0.8378 0.2629
-1.250 0.2676 0.02527 0.01231 -0.1058 0.8318 0.2663
-1.000 0.2954 0.02519 0.01213 -0.1060 0.8256 0.2702
-0.750 0.3230 0.02519 0.01202 -0.1061 0.8191 0.2746
-0.500 0.3528 0.02504 0.01185 -0.1065 0.8142 0.2798
-0.250 0.3769 0.02517 0.01199 -0.1063 0.8066 0.2873
0.000 0.4064 0.02506 0.01193 -0.1067 0.8018 0.2969
0.250 0.4302 0.02523 0.01217 -0.1064 0.7945 0.3073
0.500 0.4581 0.02520 0.01225 -0.1066 0.7890 0.3213
0.750 0.4838 0.02525 0.01249 -0.1066 0.7829 0.3424
1.000 0.5088 0.02507 0.01282 -0.1066 0.7766 0.4104
1.500 0.5569 0.02457 0.01344 -0.1050 0.7643 1.0000
1.750 0.5853 0.02488 0.01369 -0.1050 0.7595 1.0000
2.000 0.6073 0.02552 0.01431 -0.1046 0.7523 1.0000
2.250 0.6337 0.02594 0.01473 -0.1045 0.7467 1.0000
2.500 0.6582 0.02649 0.01530 -0.1042 0.7408 1.0000
2.750 0.6812 0.02712 0.01602 -0.1038 0.7341 1.0000
3.000 0.7102 0.02743 0.01641 -0.1039 0.7299 1.0000
3.250 0.7279 0.02839 0.01748 -0.1031 0.7216 1.0000
3.500 0.7554 0.02880 0.01807 -0.1031 0.7169 1.0000
3.750 0.7742 0.02975 0.01917 -0.1023 0.7093 1.0000
4.000 0.7994 0.03032 0.01993 -0.1021 0.7038 1.0000
4.250 0.8204 0.03117 0.02099 -0.1015 0.6971 1.0000
4.500 0.8425 0.03197 0.02207 -0.1010 0.6905 1.0000
4.750 0.8680 0.03258 0.02296 -0.1007 0.6852 1.0000
5.000 0.8847 0.03372 0.02441 -0.0997 0.6768 1.0000
5.250 0.9293 0.02808 0.01893 -0.0930 0.6221 1.0000
5.500 0.9476 0.02600 0.01698 -0.0874 0.5624 1.0000
5.750 0.9478 0.02544 0.01507 -0.0795 0.3075 1.0000
6.000 0.9233 0.02983 0.01761 -0.0742 0.0878 1.0000
6.250 0.9217 0.03239 0.01985 -0.0711 0.0555 1.0000
6.500 0.9264 0.03418 0.02173 -0.0684 0.0484 1.0000
6.750 0.9305 0.03614 0.02380 -0.0659 0.0440 1.0000
7.000 0.9349 0.03817 0.02597 -0.0637 0.0404 1.0000
7.250 0.9401 0.04020 0.02817 -0.0618 0.0370 1.0000
7.500 0.9436 0.04246 0.03053 -0.0599 0.0346 1.0000
7.750 0.9485 0.04465 0.03285 -0.0580 0.0334 1.0000
8.000 0.9585 0.04646 0.03486 -0.0559 0.0325 1.0000
8.250 0.9757 0.04787 0.03646 -0.0535 0.0315 1.0000
8.500 1.0125 0.04865 0.03743 -0.0513 0.0290 1.0000
8.750 1.0828 0.05095 0.03988 -0.0526 0.0259 1.0000
9.000 1.1336 0.05513 0.04436 -0.0544 0.0256 1.0000
9.250 1.1577 0.05871 0.04832 -0.0537 0.0256 1.0000
9.500 1.1722 0.06200 0.05202 -0.0521 0.0257 1.0000
9.750 1.1802 0.06521 0.05565 -0.0500 0.0260 1.0000
10.000 1.1832 0.06858 0.05941 -0.0477 0.0261 1.0000
10.250 1.1789 0.07180 0.06301 -0.0449 0.0262 1.0000
10.500 1.1702 0.07505 0.06659 -0.0422 0.0263 1.0000
10.750 1.1581 0.07843 0.07030 -0.0398 0.0264 1.0000
11.000 1.1432 0.08209 0.07427 -0.0381 0.0266 1.0000
11.250 1.1264 0.08613 0.07861 -0.0371 0.0269 1.0000
11.500 1.1082 0.09063 0.08339 -0.0369 0.0271 1.0000
11.750 1.0886 0.09563 0.08864 -0.0376 0.0275 1.0000
12.000 1.0683 0.10117 0.09440 -0.0391 0.0279 1.0000
12.250 1.0478 0.10728 0.10071 -0.0416 0.0283 1.0000
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Polar data table (+)
Polar graphs
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