GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 100,000 Max Cl/Cd: 55.65 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe308-il-100000-n5.txt Download as CSV file: xf-goe308-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3123 0.09352 0.08909 -0.0261 1.0000 0.0457
-7.250 -0.3224 0.09195 0.08761 -0.0240 1.0000 0.0462
-7.000 -0.3322 0.09029 0.08605 -0.0221 1.0000 0.0470
-6.750 -0.3403 0.08848 0.08431 -0.0206 1.0000 0.0476
-6.500 -0.3344 0.08560 0.08146 -0.0236 0.9968 0.0505
-6.000 -0.2834 0.07627 0.07205 -0.0371 0.9804 0.0561
-5.750 -0.2564 0.07225 0.06796 -0.0421 0.9717 0.0595
-5.500 -0.2134 0.06789 0.06328 -0.0551 0.9588 0.0648
-5.250 -0.1939 0.06145 0.05682 -0.0558 0.9522 0.0501
-5.000 -0.1659 0.05701 0.05220 -0.0603 0.9411 0.0507
-4.750 -0.1389 0.05265 0.04769 -0.0635 0.9320 0.0481
-4.500 -0.1082 0.04790 0.04269 -0.0673 0.9240 0.0460
-4.250 -0.0812 0.04450 0.03906 -0.0693 0.9145 0.0484
-4.000 -0.0479 0.04039 0.03463 -0.0721 0.9080 0.0489
-3.750 -0.0218 0.03682 0.03073 -0.0729 0.8979 0.0486
-3.500 0.0100 0.03306 0.02652 -0.0744 0.8906 0.0501
-3.250 0.0378 0.02959 0.02254 -0.0747 0.8811 0.0515
-3.000 0.0661 0.02663 0.01908 -0.0748 0.8717 0.0516
-2.750 0.0992 0.02390 0.01577 -0.0756 0.8641 0.0521
-2.500 0.1283 0.02203 0.01341 -0.0755 0.8531 0.0531
-2.250 0.1591 0.02114 0.01241 -0.0760 0.8423 0.0560
-2.000 0.1925 0.02002 0.01103 -0.0768 0.8318 0.0578
-1.750 0.2254 0.01889 0.00964 -0.0773 0.8203 0.0588
-1.500 0.2558 0.01802 0.00857 -0.0775 0.8068 0.0603
-1.250 0.2858 0.01731 0.00771 -0.0775 0.7927 0.0623
-1.000 0.3153 0.01672 0.00700 -0.0774 0.7776 0.0653
-0.750 0.3438 0.01638 0.00663 -0.0772 0.7615 0.0696
-0.500 0.3721 0.01605 0.00622 -0.0769 0.7448 0.0776
-0.250 0.3999 0.01586 0.00597 -0.0766 0.7263 0.0959
0.000 0.4281 0.01568 0.00571 -0.0764 0.7072 0.1215
0.250 0.4563 0.01558 0.00552 -0.0762 0.6879 0.1438
0.500 0.4840 0.01553 0.00537 -0.0759 0.6689 0.1586
0.750 0.5105 0.01553 0.00528 -0.0755 0.6494 0.1749
1.000 0.5364 0.01554 0.00521 -0.0749 0.6308 0.1939
1.250 0.5616 0.01554 0.00516 -0.0743 0.6134 0.2202
1.500 0.5862 0.01549 0.00511 -0.0736 0.5970 0.2526
2.000 0.7123 0.01446 0.00526 -0.0885 0.5598 1.0000
2.250 0.7351 0.01470 0.00534 -0.0874 0.5469 1.0000
2.500 0.7579 0.01494 0.00545 -0.0863 0.5353 1.0000
2.750 0.7804 0.01519 0.00561 -0.0852 0.5239 1.0000
3.000 0.8031 0.01544 0.00579 -0.0842 0.5138 1.0000
3.250 0.8259 0.01572 0.00595 -0.0831 0.5048 1.0000
3.500 0.8483 0.01598 0.00621 -0.0821 0.4952 1.0000
3.750 0.8707 0.01627 0.00643 -0.0810 0.4861 1.0000
4.000 0.8927 0.01656 0.00665 -0.0798 0.4764 1.0000
4.250 0.9139 0.01685 0.00694 -0.0785 0.4653 1.0000
4.500 0.9350 0.01714 0.00720 -0.0772 0.4546 1.0000
4.750 0.9564 0.01746 0.00745 -0.0760 0.4451 1.0000
5.000 0.9778 0.01777 0.00782 -0.0748 0.4361 1.0000
5.250 0.9998 0.01811 0.00817 -0.0737 0.4288 1.0000
5.500 1.0211 0.01843 0.00858 -0.0725 0.4208 1.0000
5.750 1.0428 0.01879 0.00895 -0.0714 0.4137 1.0000
6.000 1.0635 0.01913 0.00939 -0.0701 0.4053 1.0000
6.250 1.0845 0.01949 0.00983 -0.0688 0.3975 1.0000
6.500 1.1047 0.01985 0.01030 -0.0675 0.3890 1.0000
6.750 1.1252 0.02022 0.01078 -0.0661 0.3812 1.0000
7.000 1.1451 0.02059 0.01127 -0.0647 0.3727 1.0000
7.250 1.1621 0.02090 0.01172 -0.0628 0.3596 1.0000
7.500 1.1753 0.02114 0.01197 -0.0601 0.3401 1.0000
7.750 1.1884 0.02142 0.01235 -0.0575 0.3175 1.0000
8.000 1.2012 0.02181 0.01274 -0.0549 0.2960 1.0000
8.250 1.2115 0.02233 0.01321 -0.0520 0.2637 1.0000
8.500 1.2216 0.02301 0.01383 -0.0492 0.2339 1.0000
8.750 1.2232 0.02417 0.01471 -0.0453 0.1881 1.0000
9.000 1.2229 0.02556 0.01583 -0.0412 0.1474 1.0000
9.250 1.2080 0.02783 0.01749 -0.0356 0.0616 1.0000
9.500 1.1978 0.02997 0.01939 -0.0308 0.0391 1.0000
9.750 1.1960 0.03169 0.02117 -0.0273 0.0339 1.0000
10.000 1.1971 0.03329 0.02293 -0.0245 0.0305 1.0000
10.250 1.1968 0.03507 0.02487 -0.0219 0.0282 1.0000
10.500 1.1922 0.03730 0.02725 -0.0193 0.0263 1.0000
10.750 1.1862 0.03982 0.02993 -0.0172 0.0253 1.0000
11.000 1.1835 0.04223 0.03255 -0.0157 0.0248 1.0000
11.250 1.1794 0.04494 0.03545 -0.0145 0.0243 1.0000
11.500 1.1730 0.04808 0.03879 -0.0137 0.0237 1.0000
11.750 1.1662 0.05150 0.04239 -0.0134 0.0232 1.0000
12.000 1.1592 0.05515 0.04622 -0.0134 0.0225 1.0000
12.250 1.1518 0.05903 0.05026 -0.0137 0.0220 1.0000
12.500 1.1442 0.06307 0.05449 -0.0143 0.0213 1.0000
12.750 1.1377 0.06707 0.05863 -0.0149 0.0210 1.0000
13.000 1.1316 0.07108 0.06276 -0.0156 0.0204 1.0000
13.250 1.1263 0.07498 0.06677 -0.0162 0.0197 1.0000
13.500 1.1231 0.07850 0.07037 -0.0164 0.0191 1.0000
13.750 1.1242 0.08132 0.07327 -0.0163 0.0188 1.0000
14.000 1.1289 0.08342 0.07541 -0.0155 0.0183 1.0000
14.250 1.1404 0.08438 0.07636 -0.0135 0.0178 1.0000
14.500 1.1677 0.08341 0.07532 -0.0088 0.0169 1.0000
14.750 1.1689 0.08668 0.07878 -0.0093 0.0167 1.0000
15.000 1.1685 0.09027 0.08258 -0.0100 0.0163 1.0000
15.250 1.1648 0.09442 0.08695 -0.0114 0.0158 1.0000
15.500 1.1637 0.09828 0.09101 -0.0123 0.0156 1.0000
15.750 1.1586 0.10285 0.09584 -0.0139 0.0152 1.0000
16.000 1.1538 0.10751 0.10071 -0.0156 0.0151 1.0000
16.250 1.1476 0.11252 0.10592 -0.0176 0.0150 1.0000
16.500 1.1399 0.11789 0.11149 -0.0201 0.0150 1.0000
16.750 1.1311 0.12361 0.11739 -0.0229 0.0151 1.0000
17.000 1.1206 0.12988 0.12387 -0.0263 0.0151 1.0000
17.250 1.1091 0.13659 0.13075 -0.0301 0.0151 1.0000
17.500 1.0966 0.14382 0.13816 -0.0344 0.0151 1.0000
17.750 1.0844 0.15129 0.14579 -0.0390 0.0153 1.0000
18.000 1.0714 0.15934 0.15399 -0.0440 0.0154 1.0000
18.250 1.0581 0.16796 0.16273 -0.0494 0.0156 1.0000
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Polar data table (+)
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