GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.77 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe235-il-1000000.txt Download as CSV file: xf-goe235-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4684 0.09968 0.09802 0.0039 1.0000 0.0197
-8.250 -0.4665 0.09573 0.09409 -0.0002 1.0000 0.0198
-8.000 -0.4623 0.09173 0.09010 -0.0045 1.0000 0.0198
-7.750 -0.4540 0.08709 0.08547 -0.0078 1.0000 0.0199
-7.500 -0.4430 0.08405 0.08243 -0.0083 1.0000 0.0201
-7.250 -0.4301 0.08099 0.07938 -0.0105 1.0000 0.0202
-7.000 -0.4157 0.07784 0.07624 -0.0135 1.0000 0.0203
-6.750 -0.3996 0.07460 0.07300 -0.0170 1.0000 0.0205
-6.500 -0.3819 0.07127 0.06966 -0.0209 1.0000 0.0208
-6.250 -0.3566 0.06744 0.06580 -0.0266 0.9854 0.0212
-6.000 -0.3312 0.06359 0.06190 -0.0319 0.9616 0.0218
-5.750 -0.2948 0.05706 0.05516 -0.0423 0.9348 0.0233
-5.500 -0.2721 0.05300 0.05093 -0.0453 0.9033 0.0233
-5.250 -0.2325 0.03336 0.03113 -0.0452 0.8391 0.0236
-5.000 -0.2135 0.03067 0.02836 -0.0462 0.8282 0.0237
-4.750 -0.1925 0.02806 0.02567 -0.0475 0.8182 0.0239
-4.500 -0.1700 0.02551 0.02303 -0.0490 0.8100 0.0242
-4.250 -0.1597 0.03863 0.03590 -0.0530 0.8211 0.0244
-4.000 -0.1329 0.03630 0.03344 -0.0543 0.8114 0.0248
-3.750 -0.0947 0.03228 0.02907 -0.0564 0.8028 0.0272
-3.500 -0.0653 0.02937 0.02590 -0.0573 0.7950 0.0273
-3.250 -0.0402 0.02547 0.02182 -0.0586 0.7860 0.0277
-3.000 -0.0139 0.02409 0.02034 -0.0590 0.7754 0.0280
-2.750 0.0130 0.02282 0.01896 -0.0594 0.7625 0.0283
-2.500 0.0405 0.02154 0.01754 -0.0597 0.7472 0.0287
-2.250 0.0687 0.02021 0.01605 -0.0599 0.7288 0.0294
-2.000 0.1006 0.01937 0.01480 -0.0593 0.7053 0.0318
-1.750 0.1294 0.01809 0.01320 -0.0593 0.6821 0.0319
-1.500 0.1564 0.01550 0.01043 -0.0600 0.6623 0.0328
-1.250 0.1843 0.01485 0.00966 -0.0601 0.6446 0.0334
-1.000 0.2127 0.01424 0.00893 -0.0602 0.6317 0.0345
-0.750 0.2422 0.01462 0.00907 -0.0597 0.6197 0.0371
-0.500 0.2711 0.01411 0.00836 -0.0596 0.6060 0.0372
0.000 0.3293 0.01042 0.00421 -0.0596 0.5735 0.0321
0.250 0.3576 0.00976 0.00342 -0.0595 0.5446 0.0323
0.500 0.3844 0.00982 0.00302 -0.0595 0.4275 0.0328
0.750 0.4118 0.00991 0.00285 -0.0595 0.3623 0.0333
1.000 0.4386 0.01026 0.00279 -0.0596 0.2570 0.0338
1.250 0.4663 0.01034 0.00270 -0.0596 0.2192 0.0344
1.500 0.4943 0.01031 0.00261 -0.0595 0.2047 0.0353
1.750 0.5225 0.01029 0.00256 -0.0595 0.1960 0.0365
2.000 0.5506 0.01033 0.00255 -0.0594 0.1868 0.0373
2.250 0.5789 0.01014 0.00234 -0.0595 0.1791 0.0389
2.500 0.6070 0.01018 0.00235 -0.0594 0.1700 0.0404
2.750 0.6350 0.01023 0.00237 -0.0594 0.1596 0.0422
3.000 0.6628 0.01033 0.00238 -0.0593 0.1427 0.0444
3.250 0.6881 0.01114 0.00276 -0.0592 0.0409 0.0481
3.500 0.7157 0.01130 0.00291 -0.0590 0.0370 0.0516
3.750 0.7434 0.01144 0.00306 -0.0589 0.0349 0.0593
4.000 0.7667 0.00974 0.00339 -0.0584 0.0343 1.0000
4.250 0.7941 0.00997 0.00360 -0.0583 0.0333 1.0000
4.500 0.8214 0.01023 0.00384 -0.0581 0.0324 1.0000
4.750 0.8485 0.01052 0.00412 -0.0579 0.0316 1.0000
5.000 0.8755 0.01084 0.00443 -0.0577 0.0308 1.0000
5.250 0.9021 0.01122 0.00482 -0.0575 0.0301 1.0000
5.500 0.9282 0.01168 0.00531 -0.0572 0.0294 1.0000
5.750 0.9535 0.01230 0.00596 -0.0568 0.0288 1.0000
6.000 0.9799 0.01264 0.00632 -0.0565 0.0286 1.0000
6.250 1.0062 0.01297 0.00666 -0.0562 0.0283 1.0000
6.500 1.0322 0.01335 0.00705 -0.0559 0.0278 1.0000
6.750 1.0577 0.01380 0.00752 -0.0556 0.0274 1.0000
7.000 1.0828 0.01428 0.00803 -0.0552 0.0270 1.0000
7.250 1.1076 0.01480 0.00856 -0.0547 0.0266 1.0000
7.500 1.1321 0.01535 0.00913 -0.0542 0.0261 1.0000
7.750 1.1562 0.01592 0.00974 -0.0537 0.0257 1.0000
8.000 1.1799 0.01653 0.01036 -0.0532 0.0253 1.0000
8.250 1.2030 0.01719 0.01103 -0.0526 0.0248 1.0000
8.500 1.2242 0.01816 0.01200 -0.0518 0.0243 1.0000
8.750 1.2411 0.02003 0.01390 -0.0505 0.0238 1.0000
9.000 1.2643 0.02060 0.01452 -0.0499 0.0236 1.0000
9.250 1.2876 0.02109 0.01506 -0.0493 0.0233 1.0000
9.500 1.3102 0.02169 0.01572 -0.0486 0.0230 1.0000
9.750 1.3324 0.02230 0.01639 -0.0479 0.0226 1.0000
10.000 1.3540 0.02296 0.01711 -0.0472 0.0221 1.0000
10.250 1.3747 0.02375 0.01794 -0.0463 0.0217 1.0000
10.500 1.3949 0.02457 0.01881 -0.0454 0.0213 1.0000
10.750 1.4146 0.02538 0.01967 -0.0445 0.0210 1.0000
11.000 1.4335 0.02621 0.02055 -0.0436 0.0207 1.0000
11.250 1.4515 0.02708 0.02146 -0.0425 0.0204 1.0000
11.500 1.4685 0.02806 0.02247 -0.0414 0.0201 1.0000
11.750 1.4802 0.03120 0.02567 -0.0401 0.0194 1.0000
12.000 1.4950 0.03159 0.02618 -0.0386 0.0192 1.0000
12.250 1.5084 0.03236 0.02706 -0.0370 0.0190 1.0000
12.500 1.5190 0.03336 0.02819 -0.0351 0.0188 1.0000
12.750 1.5250 0.03452 0.02946 -0.0326 0.0185 1.0000
13.000 1.5298 0.03588 0.03094 -0.0304 0.0182 1.0000
13.250 1.5338 0.03740 0.03257 -0.0284 0.0180 1.0000
13.500 1.5370 0.03908 0.03435 -0.0267 0.0177 1.0000
13.750 1.5399 0.04086 0.03624 -0.0254 0.0175 1.0000
14.000 1.5426 0.04275 0.03822 -0.0245 0.0173 1.0000
14.250 1.5454 0.04469 0.04024 -0.0239 0.0171 1.0000
14.500 1.5468 0.04691 0.04255 -0.0235 0.0169 1.0000
14.750 1.5480 0.04926 0.04499 -0.0235 0.0168 1.0000
15.000 1.5483 0.05187 0.04768 -0.0237 0.0166 1.0000
15.250 1.5472 0.05480 0.05070 -0.0242 0.0165 1.0000
15.500 1.5448 0.05808 0.05408 -0.0250 0.0164 1.0000
15.750 1.5402 0.06177 0.05786 -0.0260 0.0163 1.0000
16.000 1.5335 0.06585 0.06203 -0.0272 0.0162 1.0000
16.250 1.5227 0.07063 0.06693 -0.0287 0.0160 1.0000
16.500 1.5020 0.07700 0.07347 -0.0307 0.0159 1.0000
16.750 1.4756 0.08490 0.08157 -0.0341 0.0158 1.0000
17.000 1.4614 0.09132 0.08815 -0.0376 0.0157 1.0000
17.250 1.4454 0.09838 0.09536 -0.0417 0.0157 1.0000
17.500 1.4270 0.10615 0.10329 -0.0461 0.0156 1.0000
17.750 1.4066 0.11459 0.11188 -0.0511 0.0156 1.0000
18.000 1.3831 0.12396 0.12142 -0.0568 0.0155 1.0000
18.250 1.3559 0.13463 0.13226 -0.0635 0.0155 1.0000
18.500 1.3235 0.14703 0.14484 -0.0714 0.0155 1.0000
18.750 1.2703 0.16587 0.16392 -0.0839 0.0155 1.0000
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