GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 200,000 Max Cl/Cd: 74.77 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe393-il-200000-n5.txt Download as CSV file: xf-goe393-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4629 0.10060 0.09722 0.0124 1.0000 0.0228
-8.000 -0.4576 0.09699 0.09364 0.0105 1.0000 0.0227
-7.750 -0.4524 0.09334 0.09001 0.0079 1.0000 0.0231
-7.500 -0.4463 0.08880 0.08550 0.0018 1.0000 0.0242
-7.250 -0.4339 0.08740 0.08414 0.0031 1.0000 0.0276
-7.000 -0.4225 0.08324 0.07999 -0.0010 1.0000 0.0274
-6.750 -0.4091 0.07772 0.07446 -0.0075 1.0000 0.0264
-6.500 -0.3929 0.07365 0.07039 -0.0116 1.0000 0.0266
-6.250 -0.3751 0.07064 0.06737 -0.0145 1.0000 0.0280
-6.000 -0.3546 0.06689 0.06358 -0.0189 1.0000 0.0300
-5.750 -0.3324 0.06230 0.05894 -0.0240 1.0000 0.0303
-5.500 -0.3081 0.05758 0.05413 -0.0290 1.0000 0.0306
-5.250 -0.2756 0.05162 0.04799 -0.0361 0.9916 0.0325
-5.000 -0.2330 0.04527 0.04136 -0.0440 0.9471 0.0335
-4.750 -0.2009 0.04024 0.03605 -0.0484 0.8847 0.0342
-4.500 -0.1786 0.03916 0.03472 -0.0482 0.8174 0.0355
-4.250 -0.1553 0.03753 0.03281 -0.0484 0.7768 0.0370
-4.000 -0.1274 0.03383 0.02870 -0.0501 0.7506 0.0373
-3.750 -0.0987 0.02995 0.02437 -0.0515 0.7289 0.0376
-3.500 -0.0699 0.02591 0.01981 -0.0526 0.7105 0.0382
-3.250 -0.0412 0.02156 0.01479 -0.0534 0.6948 0.0401
-3.000 -0.0132 0.01797 0.01043 -0.0536 0.6805 0.0406
-2.750 0.0143 0.01643 0.00845 -0.0535 0.6671 0.0413
-2.500 0.0418 0.01542 0.00711 -0.0532 0.6551 0.0421
-2.250 0.0692 0.01469 0.00613 -0.0529 0.6443 0.0428
-2.000 0.0967 0.01414 0.00538 -0.0526 0.6337 0.0436
-1.750 0.1242 0.01363 0.00474 -0.0524 0.6235 0.0445
-1.500 0.1516 0.01329 0.00434 -0.0521 0.6139 0.0468
-1.250 0.1791 0.01306 0.00406 -0.0519 0.6044 0.0494
-1.000 0.2067 0.01279 0.00372 -0.0516 0.5955 0.0518
-0.500 0.2618 0.01241 0.00331 -0.0511 0.5777 0.0607
-0.250 0.2895 0.01237 0.00324 -0.0508 0.5692 0.0716
0.000 0.3173 0.01238 0.00321 -0.0506 0.5603 0.0831
0.250 0.3451 0.01241 0.00315 -0.0504 0.5522 0.0918
0.500 0.3727 0.01242 0.00315 -0.0502 0.5439 0.0990
0.750 0.4003 0.01243 0.00312 -0.0500 0.5354 0.1053
1.000 0.4277 0.01245 0.00315 -0.0498 0.5270 0.1148
1.250 0.4553 0.01242 0.00314 -0.0496 0.5179 0.1234
1.500 0.4826 0.01239 0.00310 -0.0494 0.5098 0.1283
1.750 0.5102 0.01234 0.00307 -0.0492 0.5011 0.1315
2.000 0.5376 0.01233 0.00305 -0.0490 0.4931 0.1348
2.250 0.5651 0.01230 0.00305 -0.0488 0.4845 0.1394
2.500 0.5925 0.01231 0.00308 -0.0486 0.4759 0.1463
2.750 0.6198 0.01233 0.00314 -0.0484 0.4673 0.1556
3.000 0.6471 0.01233 0.00322 -0.0482 0.4574 0.1716
3.250 0.6734 0.01199 0.00336 -0.0481 0.4476 0.3782
3.750 0.7311 0.01109 0.00354 -0.0481 0.4270 1.0000
4.000 0.7580 0.01126 0.00365 -0.0478 0.4147 1.0000
4.250 0.7848 0.01144 0.00379 -0.0475 0.3999 1.0000
4.500 0.8116 0.01163 0.00394 -0.0473 0.3863 1.0000
4.750 0.8382 0.01185 0.00413 -0.0470 0.3751 1.0000
5.000 0.8650 0.01207 0.00437 -0.0467 0.3651 1.0000
5.250 0.8917 0.01229 0.00461 -0.0465 0.3541 1.0000
5.500 0.9182 0.01254 0.00487 -0.0462 0.3430 1.0000
5.750 0.9445 0.01281 0.00516 -0.0459 0.3319 1.0000
6.000 0.9709 0.01307 0.00547 -0.0456 0.3199 1.0000
6.250 0.9971 0.01335 0.00580 -0.0454 0.3060 1.0000
6.500 1.0228 0.01368 0.00614 -0.0450 0.2870 1.0000
6.750 1.0481 0.01408 0.00653 -0.0447 0.2526 1.0000
7.000 1.0699 0.01506 0.00711 -0.0443 0.1791 1.0000
7.250 1.0916 0.01612 0.00795 -0.0439 0.1413 1.0000
7.750 1.1373 0.01770 0.00941 -0.0431 0.1025 1.0000
8.000 1.1602 0.01841 0.01016 -0.0426 0.0898 1.0000
8.250 1.1827 0.01916 0.01091 -0.0422 0.0769 1.0000
8.500 1.2053 0.01987 0.01165 -0.0417 0.0602 1.0000
8.750 1.2250 0.02097 0.01261 -0.0410 0.0398 1.0000
9.000 1.2438 0.02216 0.01380 -0.0402 0.0307 1.0000
9.250 1.2612 0.02350 0.01520 -0.0393 0.0257 1.0000
9.500 1.2798 0.02457 0.01642 -0.0384 0.0226 1.0000
9.750 1.2960 0.02587 0.01780 -0.0375 0.0201 1.0000
10.000 1.3094 0.02743 0.01949 -0.0363 0.0186 1.0000
10.250 1.3232 0.02882 0.02105 -0.0351 0.0176 1.0000
10.500 1.3349 0.03032 0.02270 -0.0338 0.0166 1.0000
10.750 1.3448 0.03188 0.02439 -0.0326 0.0156 1.0000
11.000 1.3508 0.03355 0.02620 -0.0310 0.0148 1.0000
11.250 1.3520 0.03565 0.02841 -0.0296 0.0141 1.0000
11.500 1.3489 0.03849 0.03136 -0.0289 0.0136 1.0000
11.750 1.3489 0.04134 0.03435 -0.0289 0.0133 1.0000
12.000 1.3506 0.04419 0.03737 -0.0291 0.0130 1.0000
12.250 1.3513 0.04724 0.04058 -0.0294 0.0127 1.0000
12.500 1.3509 0.05046 0.04396 -0.0298 0.0124 1.0000
12.750 1.3495 0.05385 0.04751 -0.0302 0.0122 1.0000
13.000 1.3471 0.05741 0.05122 -0.0308 0.0119 1.0000
13.250 1.3436 0.06115 0.05512 -0.0314 0.0117 1.0000
13.500 1.3391 0.06510 0.05923 -0.0323 0.0115 1.0000
13.750 1.3335 0.06927 0.06356 -0.0334 0.0113 1.0000
14.000 1.3268 0.07366 0.06810 -0.0348 0.0111 1.0000
14.250 1.3192 0.07829 0.07289 -0.0363 0.0109 1.0000
14.500 1.3104 0.08316 0.07790 -0.0381 0.0108 1.0000
14.750 1.3009 0.08832 0.08324 -0.0401 0.0106 1.0000
15.000 1.2912 0.09378 0.08885 -0.0425 0.0105 1.0000
15.250 1.2810 0.09951 0.09472 -0.0451 0.0103 1.0000
15.500 1.2700 0.10566 0.10101 -0.0481 0.0103 1.0000
15.750 1.2582 0.11214 0.10764 -0.0513 0.0102 1.0000
16.000 1.2456 0.11901 0.11466 -0.0548 0.0101 1.0000
16.250 1.2317 0.12645 0.12226 -0.0588 0.0101 1.0000
16.500 1.2165 0.13458 0.13055 -0.0634 0.0101 1.0000
16.750 1.1976 0.14411 0.14024 -0.0689 0.0102 1.0000
17.000 1.1593 0.16049 0.15693 -0.0787 0.0107 1.0000
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