GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 200,000 Max Cl/Cd: 95.79 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe495-il-200000.txt Download as CSV file: xf-goe495-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 495 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3669 0.09151 0.08830 -0.0235 1.0000 0.0410
-7.000 -0.3849 0.09087 0.08774 -0.0198 1.0000 0.0415
-6.750 -0.3982 0.08959 0.08653 -0.0184 1.0000 0.0425
-6.500 -0.3738 0.08508 0.08202 -0.0333 0.9954 0.0443
-6.250 -0.3450 0.07758 0.07449 -0.0452 0.9899 0.0450
-6.000 -0.3352 0.07479 0.07172 -0.0408 0.9872 0.0468
-5.750 -0.3079 0.07169 0.06859 -0.0445 0.9840 0.0504
-5.500 -0.2440 0.06097 0.05764 -0.0727 0.9757 0.0575
-5.250 -0.2306 0.05896 0.05570 -0.0693 0.9727 0.0593
-5.000 -0.1309 0.03471 0.03143 -0.0859 0.9571 0.0717
-4.750 -0.1170 0.03316 0.02991 -0.0840 0.9496 0.0745
-4.500 -0.0747 0.02712 0.02363 -0.0952 0.9468 0.0864
-4.250 -0.0402 0.02859 0.02351 -0.1123 0.9585 0.0588
-4.000 0.0035 0.02355 0.01782 -0.1166 0.9572 0.0517
-3.750 0.0344 0.02139 0.01514 -0.1176 0.9515 0.0542
-3.500 0.0722 0.01950 0.01272 -0.1196 0.9481 0.0558
-3.250 0.1108 0.01773 0.01060 -0.1219 0.9457 0.0590
-3.000 0.1507 0.01672 0.00952 -0.1243 0.9437 0.0634
-2.750 0.1794 0.01603 0.00871 -0.1243 0.9375 0.0666
-2.500 0.2157 0.01525 0.00785 -0.1259 0.9337 0.0724
-2.250 0.2554 0.01458 0.00719 -0.1282 0.9312 0.0798
-2.000 0.2975 0.01390 0.00655 -0.1309 0.9294 0.0945
-1.750 0.3249 0.01334 0.00629 -0.1309 0.9221 0.1631
-1.500 0.3627 0.01294 0.00604 -0.1329 0.9186 0.2293
-1.250 0.4019 0.01255 0.00581 -0.1351 0.9159 0.2836
-1.000 0.4298 0.01234 0.00581 -0.1351 0.9087 0.3509
-0.750 0.4641 0.01192 0.00569 -0.1363 0.9041 0.4488
-0.500 0.4999 0.01135 0.00553 -0.1376 0.9009 0.5728
-0.250 0.5259 0.01043 0.00543 -0.1365 0.8931 1.0000
0.000 0.5612 0.01031 0.00516 -0.1377 0.8881 1.0000
0.250 0.5893 0.01034 0.00509 -0.1374 0.8798 1.0000
0.500 0.6223 0.01024 0.00490 -0.1381 0.8737 1.0000
0.750 0.6496 0.01028 0.00488 -0.1376 0.8644 1.0000
1.000 0.6813 0.01018 0.00471 -0.1379 0.8569 1.0000
1.250 0.7084 0.01017 0.00465 -0.1373 0.8460 1.0000
1.500 0.7354 0.01019 0.00462 -0.1367 0.8348 1.0000
1.750 0.7632 0.01019 0.00460 -0.1362 0.8240 1.0000
2.000 0.7912 0.01018 0.00454 -0.1357 0.8128 1.0000
2.250 0.8183 0.01021 0.00454 -0.1351 0.8010 1.0000
2.500 0.8442 0.01028 0.00462 -0.1344 0.7882 1.0000
2.750 0.8702 0.01035 0.00468 -0.1336 0.7751 1.0000
3.000 0.8963 0.01042 0.00477 -0.1330 0.7620 1.0000
3.250 0.9222 0.01049 0.00484 -0.1322 0.7478 1.0000
3.500 0.9478 0.01053 0.00490 -0.1313 0.7315 1.0000
3.750 0.9730 0.01056 0.00491 -0.1303 0.7121 1.0000
4.000 0.9969 0.01060 0.00491 -0.1290 0.6866 1.0000
4.250 1.0204 0.01070 0.00495 -0.1276 0.6578 1.0000
4.500 1.0432 0.01089 0.00508 -0.1262 0.6247 1.0000
4.750 1.0659 0.01116 0.00528 -0.1249 0.5922 1.0000
5.000 1.0879 0.01152 0.00553 -0.1234 0.5565 1.0000
5.250 1.1082 0.01196 0.00583 -0.1217 0.5103 1.0000
5.500 1.1256 0.01260 0.00621 -0.1196 0.4428 1.0000
5.750 1.1370 0.01374 0.00681 -0.1167 0.3367 1.0000
6.000 1.1422 0.01569 0.00787 -0.1133 0.1914 1.0000
6.250 1.1495 0.01778 0.00920 -0.1102 0.0912 1.0000
6.500 1.1646 0.01905 0.01034 -0.1081 0.0693 1.0000
6.750 1.1802 0.02023 0.01153 -0.1060 0.0598 1.0000
7.000 1.1934 0.02166 0.01292 -0.1037 0.0525 1.0000
7.250 1.2107 0.02270 0.01409 -0.1018 0.0473 1.0000
7.500 1.2257 0.02409 0.01549 -0.0998 0.0432 1.0000
7.750 1.2415 0.02624 0.01766 -0.0979 0.0399 1.0000
8.000 1.2616 0.02742 0.01896 -0.0966 0.0367 1.0000
8.250 1.2824 0.02902 0.02064 -0.0955 0.0342 1.0000
8.500 1.3060 0.03129 0.02297 -0.0949 0.0322 1.0000
8.750 1.3342 0.03565 0.02758 -0.0952 0.0304 1.0000
9.000 1.3507 0.03673 0.02896 -0.0932 0.0289 1.0000
9.250 1.3685 0.03915 0.03171 -0.0916 0.0278 1.0000
9.500 1.3834 0.04230 0.03525 -0.0897 0.0274 1.0000
9.750 1.3934 0.04596 0.03934 -0.0872 0.0273 1.0000
10.000 1.3978 0.05017 0.04400 -0.0843 0.0276 1.0000
10.250 1.3960 0.05476 0.04900 -0.0810 0.0283 1.0000
10.500 1.3889 0.05940 0.05400 -0.0776 0.0290 1.0000
10.750 1.3765 0.06385 0.05874 -0.0739 0.0295 1.0000
11.000 1.3864 0.06925 0.06429 -0.0730 0.0313 1.0000
11.500 1.1902 0.07734 0.07368 -0.0565 0.0368 1.0000
11.750 1.1597 0.08368 0.08022 -0.0569 0.0371 1.0000
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Polar data table (+)
Polar graphs
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