GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Reynolds number: 500,000 Max Cl/Cd: 73.86 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe235-il-500000.txt Download as CSV file: xf-goe235-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4450 0.09514 0.09283 0.0014 1.0000 0.0245
-7.750 -0.4380 0.09210 0.08981 -0.0004 1.0000 0.0249
-7.500 -0.4310 0.08901 0.08674 -0.0025 1.0000 0.0253
-7.250 -0.4215 0.08565 0.08339 -0.0058 1.0000 0.0259
-7.000 -0.4076 0.08180 0.07954 -0.0109 1.0000 0.0267
-6.750 -0.3796 0.07563 0.07330 -0.0268 1.0000 0.0273
-6.500 -0.3610 0.07057 0.06820 -0.0323 1.0000 0.0274
-6.250 -0.3497 0.06745 0.06510 -0.0319 1.0000 0.0276
-6.000 -0.3353 0.06462 0.06229 -0.0326 1.0000 0.0277
-5.750 -0.3196 0.06183 0.05950 -0.0339 1.0000 0.0280
-5.500 -0.3003 0.05889 0.05655 -0.0363 0.9981 0.0283
-5.250 -0.2656 0.05509 0.05268 -0.0423 0.9899 0.0290
-5.000 -0.2290 0.05117 0.04867 -0.0484 0.9793 0.0300
-4.750 -0.1717 0.04506 0.04210 -0.0586 0.9653 0.0319
-4.500 -0.1522 0.04117 0.03816 -0.0598 0.9469 0.0322
-4.250 -0.1340 0.03905 0.03599 -0.0595 0.9268 0.0324
-4.000 -0.1138 0.03709 0.03395 -0.0594 0.9061 0.0327
-3.750 -0.0912 0.03513 0.03186 -0.0595 0.8877 0.0333
-3.500 -0.0664 0.03307 0.02964 -0.0599 0.8717 0.0341
-3.250 -0.0390 0.03085 0.02719 -0.0604 0.8572 0.0356
-3.000 -0.0033 0.02752 0.02320 -0.0611 0.8454 0.0375
-2.750 0.0206 0.02546 0.02112 -0.0615 0.8332 0.0379
-2.500 0.0460 0.02411 0.01969 -0.0617 0.8217 0.0385
-2.250 0.0725 0.02286 0.01832 -0.0618 0.8105 0.0395
-2.000 0.1004 0.02156 0.01681 -0.0618 0.7982 0.0410
-1.750 0.1328 0.02019 0.01487 -0.0614 0.7854 0.0440
-1.500 0.1593 0.01847 0.01315 -0.0618 0.7719 0.0448
-1.250 0.1866 0.01745 0.01206 -0.0618 0.7571 0.0459
-1.000 0.2148 0.01661 0.01109 -0.0618 0.7410 0.0480
-0.750 0.2451 0.01752 0.01161 -0.0610 0.7239 0.0511
-0.500 0.2723 0.01481 0.00885 -0.0615 0.7065 0.0533
0.000 0.3287 0.01378 0.00743 -0.0612 0.6665 0.0618
0.250 0.3563 0.01307 0.00666 -0.0611 0.6462 0.0643
0.500 0.3843 0.01308 0.00648 -0.0608 0.6226 0.0694
0.750 0.4143 0.01159 0.00467 -0.0601 0.6027 0.0482
1.000 0.4427 0.01097 0.00387 -0.0597 0.5772 0.0452
1.250 0.4703 0.01074 0.00354 -0.0595 0.5326 0.0462
1.500 0.4961 0.01107 0.00335 -0.0593 0.4133 0.0475
1.750 0.5224 0.01134 0.00323 -0.0591 0.3213 0.0478
2.000 0.5487 0.01166 0.00319 -0.0590 0.2451 0.0487
2.250 0.5762 0.01173 0.00316 -0.0589 0.2247 0.0500
2.500 0.6039 0.01179 0.00316 -0.0588 0.2127 0.0513
2.750 0.6316 0.01172 0.00307 -0.0588 0.2030 0.0551
3.000 0.6595 0.01173 0.00308 -0.0588 0.1948 0.0587
3.250 0.6872 0.01178 0.00309 -0.0587 0.1853 0.0635
3.500 0.7149 0.01186 0.00313 -0.0586 0.1734 0.0741
3.750 0.7380 0.01009 0.00332 -0.0579 0.1623 1.0000
4.000 0.7652 0.01036 0.00342 -0.0578 0.1411 1.0000
4.250 0.7892 0.01137 0.00393 -0.0574 0.0494 1.0000
4.500 0.8160 0.01172 0.00423 -0.0571 0.0452 1.0000
4.750 0.8427 0.01208 0.00459 -0.0569 0.0424 1.0000
5.000 0.8694 0.01242 0.00494 -0.0566 0.0410 1.0000
5.250 0.8958 0.01280 0.00533 -0.0563 0.0400 1.0000
5.500 0.9220 0.01321 0.00576 -0.0560 0.0390 1.0000
5.750 0.9478 0.01367 0.00624 -0.0556 0.0382 1.0000
6.000 0.9733 0.01418 0.00678 -0.0552 0.0374 1.0000
6.250 0.9982 0.01476 0.00738 -0.0548 0.0368 1.0000
6.500 1.0224 0.01545 0.00809 -0.0542 0.0361 1.0000
6.750 1.0448 0.01642 0.00910 -0.0535 0.0352 1.0000
7.000 1.0676 0.01728 0.01000 -0.0528 0.0346 1.0000
7.250 1.0915 0.01792 0.01067 -0.0522 0.0343 1.0000
7.500 1.1149 0.01863 0.01143 -0.0515 0.0340 1.0000
7.750 1.1378 0.01942 0.01225 -0.0508 0.0336 1.0000
8.000 1.1604 0.02026 0.01313 -0.0501 0.0333 1.0000
8.250 1.1829 0.02111 0.01403 -0.0493 0.0327 1.0000
8.500 1.2051 0.02198 0.01493 -0.0486 0.0321 1.0000
8.750 1.2271 0.02294 0.01593 -0.0478 0.0315 1.0000
9.000 1.2488 0.02399 0.01701 -0.0470 0.0311 1.0000
9.250 1.2704 0.02511 0.01816 -0.0463 0.0307 1.0000
9.500 1.2917 0.02635 0.01944 -0.0455 0.0302 1.0000
9.750 1.3129 0.02785 0.02096 -0.0448 0.0297 1.0000
10.000 1.3345 0.03077 0.02387 -0.0445 0.0290 1.0000
10.250 1.3525 0.03234 0.02565 -0.0434 0.0285 1.0000
10.500 1.3705 0.03335 0.02684 -0.0422 0.0282 1.0000
10.750 1.3876 0.03473 0.02841 -0.0410 0.0279 1.0000
11.000 1.4034 0.03637 0.03024 -0.0397 0.0275 1.0000
11.250 1.4175 0.03812 0.03219 -0.0383 0.0271 1.0000
11.500 1.4296 0.03985 0.03410 -0.0367 0.0266 1.0000
11.750 1.4401 0.04159 0.03601 -0.0351 0.0260 1.0000
12.000 1.4492 0.04343 0.03801 -0.0335 0.0256 1.0000
12.250 1.4567 0.04538 0.04008 -0.0318 0.0252 1.0000
12.500 1.4664 0.04719 0.04194 -0.0304 0.0248 1.0000
12.750 1.4792 0.04929 0.04404 -0.0296 0.0244 1.0000
13.000 1.4802 0.05244 0.04732 -0.0277 0.0241 1.0000
13.250 1.4717 0.05615 0.05122 -0.0252 0.0240 1.0000
13.500 1.4575 0.05977 0.05505 -0.0227 0.0239 1.0000
13.750 1.4400 0.06372 0.05921 -0.0209 0.0239 1.0000
14.000 1.4210 0.06792 0.06361 -0.0201 0.0238 1.0000
14.250 1.4003 0.07258 0.06846 -0.0201 0.0238 1.0000
14.500 1.3798 0.07745 0.07352 -0.0211 0.0238 1.0000
14.750 1.3591 0.08270 0.07894 -0.0231 0.0238 1.0000
15.000 1.3381 0.08842 0.08484 -0.0260 0.0239 1.0000
15.250 1.3172 0.09454 0.09112 -0.0297 0.0239 1.0000
15.500 1.2939 0.10167 0.09843 -0.0348 0.0240 1.0000
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Polar data table (+)
Polar graphs
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