GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 200,000 Max Cl/Cd: 74.29 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe308-il-200000-n5.txt Download as CSV file: xf-goe308-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3103 0.09304 0.08978 -0.0272 1.0000 0.0193
-7.750 -0.3177 0.09088 0.08769 -0.0258 1.0000 0.0189
-7.500 -0.3203 0.08817 0.08503 -0.0263 0.9983 0.0186
-7.250 -0.3025 0.08359 0.08045 -0.0329 0.9905 0.0191
-7.000 -0.2806 0.07837 0.07520 -0.0405 0.9822 0.0201
-6.750 -0.2587 0.07311 0.06990 -0.0480 0.9734 0.0205
-6.500 -0.2354 0.06759 0.06432 -0.0552 0.9650 0.0206
-6.250 -0.2136 0.06193 0.05856 -0.0613 0.9540 0.0210
-5.750 -0.1632 0.05512 0.05161 -0.0689 0.9370 0.0239
-5.500 -0.1389 0.05150 0.04787 -0.0721 0.9258 0.0253
-5.250 -0.1114 0.04677 0.04295 -0.0761 0.9165 0.0258
-5.000 -0.0809 0.04161 0.03752 -0.0801 0.9080 0.0277
-4.750 -0.0532 0.03596 0.03150 -0.0824 0.8973 0.0295
-4.500 -0.0309 0.02945 0.02450 -0.0836 0.8874 0.0307
-4.250 -0.0003 0.02895 0.02392 -0.0850 0.8784 0.0327
-4.000 0.0260 0.02630 0.02097 -0.0854 0.8672 0.0343
-3.750 0.0499 0.02183 0.01586 -0.0850 0.8562 0.0353
-3.500 0.0773 0.01955 0.01306 -0.0850 0.8452 0.0370
-3.250 0.1059 0.01786 0.01091 -0.0850 0.8339 0.0383
-3.000 0.1334 0.01660 0.00929 -0.0847 0.8215 0.0388
-2.750 0.1609 0.01567 0.00807 -0.0844 0.8083 0.0394
-2.500 0.1882 0.01496 0.00712 -0.0841 0.7946 0.0400
-2.250 0.2151 0.01439 0.00635 -0.0837 0.7804 0.0404
-2.000 0.2414 0.01383 0.00565 -0.0832 0.7655 0.0417
-1.750 0.2669 0.01331 0.00501 -0.0825 0.7492 0.0431
-1.500 0.2923 0.01297 0.00455 -0.0818 0.7315 0.0436
-1.250 0.3173 0.01270 0.00416 -0.0810 0.7126 0.0443
-1.000 0.3419 0.01248 0.00384 -0.0801 0.6927 0.0454
-0.750 0.3664 0.01234 0.00356 -0.0792 0.6722 0.0468
-0.500 0.3905 0.01224 0.00333 -0.0782 0.6515 0.0485
-0.250 0.4144 0.01219 0.00315 -0.0772 0.6311 0.0512
0.000 0.4380 0.01213 0.00305 -0.0762 0.6119 0.0584
0.250 0.4618 0.01216 0.00308 -0.0753 0.5933 0.0847
0.500 0.4861 0.01227 0.00306 -0.0744 0.5747 0.1018
0.750 0.5098 0.01233 0.00304 -0.0735 0.5571 0.1134
1.000 0.5334 0.01238 0.00305 -0.0726 0.5412 0.1250
1.250 0.5570 0.01244 0.00306 -0.0718 0.5261 0.1353
1.500 0.5808 0.01252 0.00308 -0.0709 0.5122 0.1412
1.750 0.6045 0.01261 0.00313 -0.0701 0.4995 0.1489
2.000 0.6280 0.01269 0.00322 -0.0692 0.4891 0.1713
2.250 0.6514 0.01271 0.00332 -0.0684 0.4790 0.2157
2.500 0.6696 0.01206 0.00344 -0.0666 0.4706 0.5614
2.750 0.7770 0.01183 0.00389 -0.0838 0.4545 0.9921
3.000 0.8172 0.01207 0.00402 -0.0867 0.4434 1.0000
3.250 0.8390 0.01226 0.00415 -0.0855 0.4342 1.0000
3.500 0.8607 0.01246 0.00431 -0.0843 0.4256 1.0000
3.750 0.8823 0.01268 0.00447 -0.0831 0.4176 1.0000
4.000 0.9042 0.01287 0.00465 -0.0819 0.4106 1.0000
4.250 0.9260 0.01307 0.00485 -0.0807 0.4040 1.0000
4.500 0.9477 0.01329 0.00506 -0.0795 0.3981 1.0000
4.750 0.9696 0.01348 0.00527 -0.0784 0.3913 1.0000
5.000 0.9907 0.01372 0.00550 -0.0771 0.3852 1.0000
5.250 1.0128 0.01390 0.00576 -0.0760 0.3789 1.0000
5.500 1.0340 0.01413 0.00601 -0.0747 0.3728 1.0000
5.750 1.0554 0.01435 0.00628 -0.0735 0.3667 1.0000
6.000 1.0766 0.01457 0.00658 -0.0723 0.3597 1.0000
6.250 1.0965 0.01479 0.00684 -0.0708 0.3491 1.0000
6.500 1.1151 0.01501 0.00708 -0.0691 0.3338 1.0000
6.750 1.1325 0.01528 0.00732 -0.0671 0.3137 1.0000
7.000 1.1492 0.01561 0.00760 -0.0651 0.2900 1.0000
7.250 1.1648 0.01602 0.00797 -0.0630 0.2659 1.0000
7.500 1.1780 0.01659 0.00840 -0.0605 0.2322 1.0000
7.750 1.1852 0.01756 0.00905 -0.0571 0.1855 1.0000
8.000 1.1935 0.01852 0.00981 -0.0540 0.1514 1.0000
8.250 1.1864 0.02042 0.01109 -0.0487 0.0599 1.0000
8.500 1.1826 0.02189 0.01236 -0.0437 0.0282 1.0000
8.750 1.1903 0.02273 0.01328 -0.0404 0.0231 1.0000
9.000 1.1987 0.02358 0.01426 -0.0374 0.0205 1.0000
9.250 1.2055 0.02457 0.01538 -0.0344 0.0187 1.0000
9.500 1.2096 0.02577 0.01675 -0.0312 0.0172 1.0000
9.750 1.2162 0.02684 0.01796 -0.0285 0.0163 1.0000
10.000 1.2225 0.02796 0.01922 -0.0260 0.0151 1.0000
10.250 1.2261 0.02932 0.02072 -0.0234 0.0146 1.0000
10.500 1.2271 0.03094 0.02249 -0.0209 0.0139 1.0000
10.750 1.2268 0.03276 0.02445 -0.0187 0.0135 1.0000
11.000 1.2250 0.03484 0.02666 -0.0167 0.0131 1.0000
11.250 1.2221 0.03718 0.02913 -0.0151 0.0129 1.0000
11.500 1.2172 0.03989 0.03197 -0.0138 0.0125 1.0000
11.750 1.2122 0.04279 0.03498 -0.0128 0.0122 1.0000
12.000 1.2065 0.04594 0.03823 -0.0122 0.0119 1.0000
12.250 1.1998 0.04932 0.04171 -0.0117 0.0116 1.0000
12.500 1.1909 0.05298 0.04542 -0.0111 0.0112 1.0000
12.750 1.1918 0.05568 0.04822 -0.0108 0.0110 1.0000
13.000 1.1940 0.05835 0.05102 -0.0108 0.0106 1.0000
13.250 1.1948 0.06113 0.05389 -0.0105 0.0103 1.0000
13.500 1.1961 0.06390 0.05677 -0.0103 0.0099 1.0000
13.750 1.1987 0.06649 0.05945 -0.0099 0.0098 1.0000
14.000 1.2012 0.06917 0.06223 -0.0096 0.0095 1.0000
14.250 1.2048 0.07173 0.06489 -0.0092 0.0094 1.0000
14.500 1.2071 0.07457 0.06784 -0.0090 0.0091 1.0000
14.750 1.2091 0.07750 0.07093 -0.0090 0.0090 1.0000
15.000 1.2103 0.08062 0.07418 -0.0092 0.0089 1.0000
15.250 1.2102 0.08399 0.07769 -0.0095 0.0087 1.0000
15.500 1.2096 0.08753 0.08138 -0.0101 0.0086 1.0000
15.750 1.2068 0.09144 0.08543 -0.0111 0.0084 1.0000
16.000 1.2032 0.09556 0.08969 -0.0124 0.0083 1.0000
16.250 1.1987 0.09987 0.09414 -0.0139 0.0082 1.0000
16.500 1.1944 0.10418 0.09856 -0.0156 0.0080 1.0000
16.750 1.1872 0.10929 0.10389 -0.0175 0.0081 1.0000
17.000 1.1829 0.11368 0.10834 -0.0195 0.0078 1.0000
17.250 1.1755 0.11887 0.11367 -0.0218 0.0077 1.0000
17.500 1.1639 0.12499 0.11994 -0.0248 0.0075 1.0000
17.750 1.1552 0.13076 0.12586 -0.0278 0.0075 1.0000
18.000 1.1443 0.13729 0.13258 -0.0317 0.0075 1.0000
18.250 1.1335 0.14401 0.13947 -0.0357 0.0075 1.0000
18.500 1.1258 0.14997 0.14554 -0.0389 0.0075 1.0000
18.750 1.1114 0.15825 0.15402 -0.0444 0.0075 1.0000
19.000 1.1025 0.16504 0.16092 -0.0485 0.0075 1.0000
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Polar data table (+)
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