GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 100,000 Max Cl/Cd: 58.32 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe310-il-100000-n5.txt Download as CSV file: xf-goe310-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3488 0.09333 0.08885 -0.0310 1.0000 0.0629
-7.500 -0.3671 0.09227 0.08790 -0.0290 1.0000 0.0635
-7.250 -0.3883 0.09135 0.08708 -0.0308 1.0000 0.0646
-6.750 -0.3554 0.08365 0.07938 -0.0300 0.9934 0.0726
-6.250 -0.3115 0.06727 0.06275 -0.0495 0.9753 0.0408
-6.000 -0.2907 0.06246 0.05785 -0.0536 0.9666 0.0393
-5.750 -0.2664 0.05663 0.05182 -0.0592 0.9579 0.0401
-5.500 -0.2381 0.04988 0.04481 -0.0652 0.9507 0.0406
-5.250 -0.2169 0.04354 0.03816 -0.0683 0.9411 0.0399
-5.000 -0.1900 0.03528 0.02916 -0.0724 0.9351 0.0397
-4.750 -0.1696 0.03076 0.02378 -0.0726 0.9251 0.0417
-4.500 -0.1373 0.02765 0.01993 -0.0741 0.9203 0.0425
-4.250 -0.1136 0.02533 0.01720 -0.0735 0.9109 0.0432
-4.000 -0.0801 0.02358 0.01523 -0.0749 0.9057 0.0456
-3.750 -0.0534 0.02240 0.01379 -0.0747 0.8961 0.0478
-3.500 -0.0183 0.02108 0.01218 -0.0758 0.8905 0.0487
-3.250 0.0087 0.02018 0.01109 -0.0754 0.8801 0.0496
-3.000 0.0403 0.01935 0.01008 -0.0759 0.8719 0.0506
-2.750 0.0706 0.01871 0.00925 -0.0761 0.8625 0.0529
-2.500 0.0978 0.01804 0.00854 -0.0758 0.8515 0.0557
-2.250 0.1279 0.01753 0.00793 -0.0760 0.8416 0.0575
-2.000 0.1594 0.01706 0.00733 -0.0763 0.8318 0.0598
-1.750 0.1873 0.01669 0.00689 -0.0761 0.8195 0.0630
-1.500 0.2163 0.01629 0.00650 -0.0761 0.8079 0.0707
-1.250 0.2474 0.01587 0.00628 -0.0765 0.7972 0.1138
-1.000 0.2790 0.01575 0.00617 -0.0770 0.7868 0.1613
-0.750 0.3074 0.01576 0.00610 -0.0768 0.7745 0.1878
-0.500 0.3367 0.01572 0.00595 -0.0769 0.7632 0.2019
-0.250 0.3671 0.01565 0.00579 -0.0772 0.7529 0.2138
0.000 0.3970 0.01558 0.00567 -0.0775 0.7426 0.2300
0.250 0.4250 0.01554 0.00557 -0.0774 0.7317 0.2397
0.750 0.4815 0.01544 0.00544 -0.0774 0.7127 0.2703
1.000 0.5071 0.01543 0.00551 -0.0769 0.7028 0.2980
1.250 0.5340 0.01538 0.00554 -0.0766 0.6946 0.3312
1.500 0.5587 0.01534 0.00559 -0.0760 0.6852 0.3679
1.750 0.5834 0.01514 0.00558 -0.0754 0.6771 0.4386
2.000 0.6970 0.01424 0.00567 -0.0935 0.6651 1.0000
2.250 0.7198 0.01441 0.00575 -0.0924 0.6527 1.0000
2.500 0.7424 0.01458 0.00585 -0.0912 0.6398 1.0000
2.750 0.7649 0.01476 0.00596 -0.0899 0.6267 1.0000
3.000 0.7874 0.01494 0.00608 -0.0887 0.6142 1.0000
3.250 0.8089 0.01510 0.00618 -0.0873 0.5988 1.0000
3.500 0.8297 0.01527 0.00628 -0.0857 0.5816 1.0000
3.750 0.8500 0.01545 0.00641 -0.0840 0.5632 1.0000
4.000 0.8703 0.01563 0.00653 -0.0823 0.5452 1.0000
4.250 0.8908 0.01584 0.00670 -0.0808 0.5286 1.0000
4.500 0.9115 0.01605 0.00694 -0.0793 0.5142 1.0000
4.750 0.9322 0.01628 0.00722 -0.0779 0.4995 1.0000
5.000 0.9525 0.01651 0.00749 -0.0763 0.4842 1.0000
5.250 0.9725 0.01677 0.00777 -0.0748 0.4678 1.0000
5.500 0.9920 0.01703 0.00809 -0.0732 0.4488 1.0000
5.750 1.0106 0.01733 0.00842 -0.0713 0.4257 1.0000
6.000 1.0282 0.01768 0.00875 -0.0694 0.3980 1.0000
6.250 1.0440 0.01812 0.00910 -0.0671 0.3660 1.0000
6.500 1.0579 0.01869 0.00952 -0.0646 0.3300 1.0000
6.750 1.0715 0.01933 0.01007 -0.0622 0.2990 1.0000
7.250 1.0992 0.02062 0.01130 -0.0574 0.2521 1.0000
7.500 1.1124 0.02131 0.01199 -0.0550 0.2319 1.0000
7.750 1.1251 0.02202 0.01271 -0.0525 0.2129 1.0000
8.000 1.1342 0.02292 0.01353 -0.0496 0.1852 1.0000
8.250 1.1396 0.02403 0.01450 -0.0462 0.1443 1.0000
8.500 1.1344 0.02564 0.01564 -0.0414 0.0844 1.0000
8.750 1.1317 0.02719 0.01694 -0.0372 0.0707 1.0000
9.000 1.1326 0.02863 0.01839 -0.0336 0.0638 1.0000
9.250 1.1328 0.03019 0.02004 -0.0302 0.0593 1.0000
9.500 1.1320 0.03189 0.02187 -0.0269 0.0551 1.0000
9.750 1.1324 0.03361 0.02375 -0.0241 0.0504 1.0000
10.000 1.1259 0.03592 0.02613 -0.0211 0.0470 1.0000
10.250 1.1302 0.03758 0.02800 -0.0190 0.0421 1.0000
10.500 1.1292 0.03972 0.03021 -0.0168 0.0389 1.0000
10.750 1.1330 0.04160 0.03227 -0.0150 0.0352 1.0000
11.000 1.1372 0.04348 0.03427 -0.0136 0.0322 1.0000
11.250 1.1408 0.04547 0.03632 -0.0123 0.0299 1.0000
11.500 1.1475 0.04740 0.03841 -0.0107 0.0278 1.0000
11.750 1.1543 0.04934 0.04046 -0.0094 0.0262 1.0000
12.000 1.1598 0.05135 0.04257 -0.0084 0.0249 1.0000
12.250 1.1630 0.05356 0.04482 -0.0077 0.0237 1.0000
12.500 1.1731 0.05560 0.04707 -0.0063 0.0221 1.0000
12.750 1.1804 0.05788 0.04957 -0.0052 0.0207 1.0000
13.000 1.1876 0.06031 0.05217 -0.0042 0.0201 1.0000
13.250 1.1920 0.06300 0.05505 -0.0034 0.0194 1.0000
13.500 1.1940 0.06593 0.05816 -0.0028 0.0190 1.0000
13.750 1.1930 0.06914 0.06156 -0.0024 0.0185 1.0000
14.000 1.1902 0.07257 0.06517 -0.0023 0.0182 1.0000
14.250 1.1854 0.07636 0.06914 -0.0025 0.0179 1.0000
14.500 1.1778 0.08051 0.07345 -0.0030 0.0175 1.0000
14.750 1.1682 0.08515 0.07828 -0.0038 0.0173 1.0000
15.000 1.1546 0.09044 0.08383 -0.0053 0.0172 1.0000
15.250 1.1405 0.09601 0.08964 -0.0072 0.0171 1.0000
15.500 1.1242 0.10221 0.09607 -0.0098 0.0171 1.0000
15.750 1.1075 0.10880 0.10288 -0.0130 0.0170 1.0000
16.000 1.0917 0.11563 0.10988 -0.0164 0.0171 1.0000
16.250 1.0718 0.12377 0.11822 -0.0212 0.0171 1.0000
16.500 1.0547 0.13182 0.12642 -0.0259 0.0172 1.0000
16.750 1.0014 0.15250 0.14746 -0.0389 0.0190 1.0000
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Polar data table (+)
Polar graphs
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