GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Reynolds number: 500,000 Max Cl/Cd: 68.84 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe235-il-500000-n5.txt Download as CSV file: xf-goe235-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 235 (SCHTTE-LANZ) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4807 0.10918 0.10678 0.0073 1.0000 0.0210
-9.000 -0.4759 0.10558 0.10318 0.0050 1.0000 0.0211
-8.750 -0.4724 0.10181 0.09943 0.0021 1.0000 0.0211
-8.500 -0.4660 0.09830 0.09593 0.0008 1.0000 0.0212
-8.250 -0.4566 0.09560 0.09325 0.0006 1.0000 0.0214
-8.000 -0.4484 0.09289 0.09056 -0.0005 1.0000 0.0216
-7.750 -0.4407 0.09006 0.08775 -0.0021 1.0000 0.0219
-7.500 -0.4329 0.08712 0.08483 -0.0042 1.0000 0.0221
-7.250 -0.4216 0.08388 0.08160 -0.0075 1.0000 0.0226
-7.000 -0.4083 0.08042 0.07814 -0.0114 1.0000 0.0232
-6.750 -0.3892 0.07569 0.07339 -0.0191 0.9943 0.0245
-6.500 -0.3605 0.07004 0.06767 -0.0291 0.9693 0.0247
-6.250 -0.3330 0.06449 0.06201 -0.0374 0.9494 0.0248
-6.000 -0.3108 0.06018 0.05760 -0.0416 0.9295 0.0248
-5.750 -0.2889 0.05609 0.05338 -0.0449 0.9056 0.0248
-5.500 -0.2702 0.05243 0.04957 -0.0468 0.8816 0.0249
-5.250 -0.2534 0.05034 0.04738 -0.0469 0.8609 0.0251
-5.000 -0.2329 0.04814 0.04506 -0.0478 0.8427 0.0253
-4.750 -0.2095 0.04570 0.04249 -0.0494 0.8273 0.0256
-4.500 -0.1843 0.04317 0.03980 -0.0511 0.8142 0.0261
-4.250 -0.1577 0.04081 0.03730 -0.0528 0.8028 0.0274
-4.000 -0.1192 0.03576 0.03185 -0.0563 0.7934 0.0288
-3.750 -0.0905 0.02914 0.02479 -0.0586 0.7843 0.0249
-3.500 -0.0627 0.02652 0.02192 -0.0592 0.7717 0.0249
-3.250 -0.0362 0.02473 0.01995 -0.0598 0.7565 0.0251
-3.000 -0.0096 0.02379 0.01892 -0.0601 0.7409 0.0254
-2.750 0.0175 0.02275 0.01774 -0.0603 0.7238 0.0259
-2.500 0.0465 0.02054 0.01519 -0.0605 0.7038 0.0259
-2.250 0.0753 0.01856 0.01285 -0.0606 0.6802 0.0259
-2.000 0.1037 0.01723 0.01121 -0.0606 0.6600 0.0261
-1.750 0.1322 0.01607 0.00979 -0.0606 0.6446 0.0264
-1.500 0.1607 0.01505 0.00852 -0.0606 0.6305 0.0267
-1.250 0.1893 0.01410 0.00735 -0.0605 0.6179 0.0271
-1.000 0.2178 0.01328 0.00632 -0.0604 0.6049 0.0277
-0.750 0.2463 0.01252 0.00534 -0.0603 0.5923 0.0285
-0.500 0.2748 0.01189 0.00457 -0.0602 0.5789 0.0288
-0.250 0.3028 0.01142 0.00396 -0.0601 0.5525 0.0292
0.000 0.3297 0.01139 0.00356 -0.0600 0.4588 0.0296
0.250 0.3566 0.01157 0.00342 -0.0599 0.3867 0.0301
0.500 0.3839 0.01166 0.00327 -0.0599 0.3280 0.0307
0.750 0.4103 0.01202 0.00321 -0.0599 0.2327 0.0313
1.000 0.4380 0.01200 0.00309 -0.0598 0.2112 0.0320
1.250 0.4658 0.01199 0.00301 -0.0598 0.1988 0.0332
1.500 0.4937 0.01194 0.00291 -0.0597 0.1893 0.0341
1.750 0.5217 0.01187 0.00284 -0.0596 0.1826 0.0350
2.000 0.5496 0.01186 0.00283 -0.0596 0.1766 0.0360
2.250 0.5774 0.01191 0.00283 -0.0595 0.1677 0.0373
2.500 0.6054 0.01191 0.00284 -0.0594 0.1617 0.0387
2.750 0.6331 0.01198 0.00287 -0.0594 0.1528 0.0405
3.000 0.6608 0.01206 0.00294 -0.0593 0.1417 0.0434
3.250 0.6855 0.01291 0.00333 -0.0590 0.0418 0.0458
3.500 0.7127 0.01308 0.00348 -0.0589 0.0370 0.0499
3.750 0.7401 0.01324 0.00365 -0.0587 0.0350 0.0556
4.250 0.7902 0.01176 0.00419 -0.0579 0.0332 1.0000
4.500 0.8172 0.01203 0.00444 -0.0577 0.0324 1.0000
4.750 0.8441 0.01233 0.00472 -0.0575 0.0317 1.0000
5.000 0.8707 0.01266 0.00505 -0.0572 0.0311 1.0000
5.250 0.8970 0.01303 0.00542 -0.0570 0.0305 1.0000
5.500 0.9230 0.01347 0.00586 -0.0566 0.0298 1.0000
5.750 0.9487 0.01392 0.00632 -0.0563 0.0292 1.0000
6.000 0.9748 0.01429 0.00670 -0.0560 0.0288 1.0000
6.250 1.0004 0.01470 0.00713 -0.0557 0.0284 1.0000
6.500 1.0258 0.01515 0.00761 -0.0553 0.0281 1.0000
6.750 1.0509 0.01563 0.00811 -0.0549 0.0277 1.0000
7.000 1.0756 0.01613 0.00864 -0.0545 0.0273 1.0000
7.250 1.1000 0.01667 0.00921 -0.0540 0.0270 1.0000
7.500 1.1240 0.01724 0.00981 -0.0535 0.0266 1.0000
7.750 1.1477 0.01783 0.01043 -0.0529 0.0262 1.0000
8.000 1.1710 0.01844 0.01106 -0.0524 0.0258 1.0000
8.250 1.1937 0.01911 0.01176 -0.0517 0.0253 1.0000
8.500 1.2153 0.01989 0.01257 -0.0510 0.0249 1.0000
8.750 1.2354 0.02087 0.01358 -0.0501 0.0246 1.0000
9.000 1.2550 0.02192 0.01466 -0.0491 0.0242 1.0000
9.250 1.2766 0.02260 0.01541 -0.0484 0.0240 1.0000
9.500 1.2978 0.02330 0.01618 -0.0476 0.0238 1.0000
9.750 1.3186 0.02401 0.01696 -0.0467 0.0234 1.0000
10.000 1.3386 0.02478 0.01781 -0.0458 0.0230 1.0000
10.250 1.3577 0.02563 0.01874 -0.0448 0.0226 1.0000
10.500 1.3759 0.02655 0.01973 -0.0437 0.0223 1.0000
10.750 1.3933 0.02749 0.02075 -0.0426 0.0219 1.0000
11.000 1.4099 0.02845 0.02179 -0.0414 0.0216 1.0000
11.250 1.4257 0.02938 0.02279 -0.0401 0.0212 1.0000
11.500 1.4404 0.03033 0.02380 -0.0388 0.0209 1.0000
11.750 1.4525 0.03133 0.02485 -0.0371 0.0207 1.0000
12.000 1.4614 0.03246 0.02604 -0.0351 0.0204 1.0000
12.250 1.4688 0.03389 0.02753 -0.0331 0.0202 1.0000
12.500 1.4750 0.03554 0.02927 -0.0313 0.0200 1.0000
12.750 1.4815 0.03701 0.03088 -0.0297 0.0198 1.0000
13.000 1.4868 0.03867 0.03270 -0.0283 0.0195 1.0000
13.250 1.4910 0.04056 0.03474 -0.0272 0.0192 1.0000
13.500 1.4943 0.04263 0.03697 -0.0264 0.0189 1.0000
13.750 1.4966 0.04488 0.03937 -0.0257 0.0186 1.0000
14.000 1.4978 0.04735 0.04198 -0.0254 0.0183 1.0000
14.250 1.4981 0.05003 0.04479 -0.0252 0.0180 1.0000
14.500 1.4972 0.05296 0.04786 -0.0254 0.0178 1.0000
14.750 1.4953 0.05616 0.05118 -0.0259 0.0176 1.0000
15.000 1.4924 0.05962 0.05477 -0.0267 0.0175 1.0000
15.250 1.4883 0.06335 0.05863 -0.0278 0.0173 1.0000
15.500 1.4829 0.06737 0.06277 -0.0291 0.0172 1.0000
15.750 1.4765 0.07169 0.06721 -0.0307 0.0171 1.0000
16.000 1.4688 0.07632 0.07196 -0.0326 0.0170 1.0000
16.250 1.4607 0.08128 0.07704 -0.0349 0.0169 1.0000
16.500 1.4518 0.08662 0.08251 -0.0375 0.0168 1.0000
16.750 1.4424 0.09223 0.08822 -0.0404 0.0167 1.0000
17.000 1.4318 0.09817 0.09428 -0.0434 0.0166 1.0000
17.250 1.4208 0.10433 0.10056 -0.0467 0.0165 1.0000
17.500 1.4086 0.11084 0.10717 -0.0502 0.0165 1.0000
18.000 1.3740 0.12649 0.12313 -0.0591 0.0163 1.0000
18.250 1.3501 0.13631 0.13315 -0.0650 0.0162 1.0000
18.500 1.3202 0.14796 0.14501 -0.0722 0.0160 1.0000
18.750 1.2765 0.16400 0.16132 -0.0827 0.0159 1.0000
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