RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 6 AIRFOIL (raf6-il) Reynolds number: 50,000 Max Cl/Cd: 35.74 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf6-il-50000.txt Download as CSV file: xf-raf6-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 6 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4220 0.10541 0.09915 -0.0219 1.0000 0.1898
-7.500 -0.4001 0.10044 0.09418 -0.0187 1.0000 0.2024
-7.250 -0.4298 0.09990 0.09382 -0.0200 1.0000 0.2055
-7.000 -0.4148 0.09568 0.08964 -0.0160 1.0000 0.2186
-6.750 -0.4147 0.09261 0.08666 -0.0139 1.0000 0.2282
-6.500 -0.4396 0.09171 0.08586 -0.0162 1.0000 0.2369
-6.250 -0.4363 0.08856 0.08279 -0.0132 1.0000 0.2520
-6.000 -0.4385 0.08591 0.08021 -0.0112 1.0000 0.2677
-5.750 -0.4421 0.08326 0.07764 -0.0096 1.0000 0.2847
-5.500 -0.4319 0.07999 0.07446 -0.0037 1.0000 0.3069
-5.250 -0.4382 0.07774 0.07227 -0.0015 1.0000 0.3333
-5.000 0.0298 0.05195 0.04524 -0.0307 1.0000 1.0000
-4.750 0.0358 0.05010 0.04347 -0.0305 1.0000 1.0000
-4.500 0.0415 0.04832 0.04176 -0.0301 1.0000 1.0000
-4.250 -0.0020 0.04958 0.04325 -0.0178 1.0000 0.9768
-4.000 -0.0629 0.05170 0.04564 -0.0026 1.0000 0.9410
-3.750 -0.1177 0.05259 0.04679 0.0095 1.0000 0.8975
-3.500 -0.1717 0.05329 0.04772 0.0205 1.0000 0.8642
-3.250 -0.2229 0.05338 0.04803 0.0300 1.0000 0.8332
-2.500 -0.1947 0.04034 0.03200 -0.0336 1.0000 0.2034
-2.250 -0.1585 0.03829 0.02916 -0.0344 1.0000 0.1736
-2.000 -0.1275 0.03641 0.02677 -0.0345 1.0000 0.1576
-1.750 -0.0990 0.03457 0.02462 -0.0344 1.0000 0.1490
-1.500 -0.0703 0.03360 0.02311 -0.0340 1.0000 0.1444
-1.250 -0.0439 0.03240 0.02173 -0.0338 1.0000 0.1458
-1.000 -0.0176 0.03156 0.02064 -0.0333 1.0000 0.1455
-0.750 0.0077 0.03079 0.01975 -0.0327 1.0000 0.1472
-0.500 0.0332 0.03032 0.01917 -0.0321 1.0000 0.1549
-0.250 0.0597 0.02993 0.01869 -0.0318 1.0000 0.1619
0.000 0.0852 0.02971 0.01841 -0.0316 1.0000 0.1735
0.250 0.1118 0.02946 0.01828 -0.0319 1.0000 0.1959
0.750 0.1536 0.02729 0.01843 -0.0297 1.0000 1.0000
1.000 0.1726 0.02817 0.01886 -0.0291 1.0000 1.0000
1.250 0.2475 0.02973 0.01988 -0.0391 0.9749 1.0000
1.500 0.3189 0.03057 0.02043 -0.0477 0.9454 1.0000
1.750 0.3798 0.03082 0.02052 -0.0539 0.9163 1.0000
2.000 0.4378 0.03064 0.02026 -0.0588 0.8871 1.0000
2.250 0.4956 0.03003 0.01961 -0.0630 0.8574 1.0000
2.500 0.5549 0.02892 0.01852 -0.0666 0.8274 1.0000
2.750 0.6181 0.02720 0.01684 -0.0700 0.7971 1.0000
3.000 0.6799 0.02529 0.01497 -0.0725 0.7603 1.0000
3.250 0.7329 0.02366 0.01324 -0.0736 0.7118 1.0000
3.500 0.7726 0.02288 0.01218 -0.0731 0.6540 1.0000
3.750 0.8076 0.02292 0.01182 -0.0728 0.6008 1.0000
4.000 0.8399 0.02350 0.01200 -0.0727 0.5587 1.0000
4.250 0.8687 0.02438 0.01261 -0.0724 0.5262 1.0000
4.500 0.8987 0.02533 0.01334 -0.0726 0.5010 1.0000
4.750 0.9237 0.02638 0.01432 -0.0721 0.4797 1.0000
5.000 0.9498 0.02747 0.01535 -0.0718 0.4619 1.0000
5.250 0.9751 0.02861 0.01647 -0.0714 0.4466 1.0000
5.500 0.9996 0.02980 0.01769 -0.0710 0.4327 1.0000
5.750 1.0244 0.03104 0.01894 -0.0706 0.4205 1.0000
6.000 1.0498 0.03231 0.02020 -0.0703 0.4093 1.0000
6.250 1.0682 0.03372 0.02182 -0.0690 0.3984 1.0000
6.500 1.0892 0.03519 0.02344 -0.0681 0.3888 1.0000
6.750 1.1117 0.03664 0.02497 -0.0674 0.3797 1.0000
7.000 1.1260 0.03843 0.02704 -0.0657 0.3714 1.0000
7.250 1.1514 0.03986 0.02846 -0.0654 0.3629 1.0000
7.500 1.1581 0.04208 0.03112 -0.0629 0.3559 1.0000
7.750 1.1790 0.04382 0.03296 -0.0622 0.3490 1.0000
8.000 1.1855 0.04632 0.03579 -0.0598 0.3430 1.0000
8.250 1.1937 0.04869 0.03843 -0.0578 0.3365 1.0000
8.500 1.2128 0.05077 0.04061 -0.0569 0.3308 1.0000
8.750 1.1990 0.05474 0.04502 -0.0532 0.3275 1.0000
9.000 1.1838 0.05901 0.04963 -0.0498 0.3246 1.0000
9.250 1.1649 0.06367 0.05453 -0.0467 0.3221 1.0000
9.500 1.1508 0.06817 0.05919 -0.0443 0.3195 1.0000
9.750 1.1514 0.07196 0.06308 -0.0429 0.3162 1.0000
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