OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF117 AIRFOIL (oaf117-il) Reynolds number: 200,000 Max Cl/Cd: 62.97 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf117-il-200000-n5.txt Download as CSV file: xf-oaf117-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF117 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9740 0.07513 0.07083 -0.0044 1.0000 0.0277
-12.750 -1.0119 0.06365 0.05911 -0.0137 1.0000 0.0275
-12.500 -1.0346 0.05502 0.05024 -0.0216 1.0000 0.0276
-12.250 -1.0497 0.04793 0.04291 -0.0291 1.0000 0.0278
-12.000 -1.0518 0.04259 0.03725 -0.0357 1.0000 0.0282
-11.750 -1.0447 0.03901 0.03331 -0.0385 1.0000 0.0289
-11.500 -1.0314 0.03633 0.03035 -0.0401 1.0000 0.0296
-11.250 -1.0126 0.03467 0.02864 -0.0409 1.0000 0.0302
-10.750 -0.9707 0.03163 0.02535 -0.0424 1.0000 0.0320
-10.500 -0.9482 0.03007 0.02356 -0.0431 1.0000 0.0332
-10.250 -0.9248 0.02852 0.02174 -0.0437 1.0000 0.0343
-10.000 -0.9006 0.02730 0.02050 -0.0443 1.0000 0.0353
-9.750 -0.8752 0.02623 0.01936 -0.0448 1.0000 0.0364
-9.500 -0.8493 0.02518 0.01819 -0.0453 1.0000 0.0378
-9.250 -0.8227 0.02415 0.01696 -0.0457 1.0000 0.0394
-9.000 -0.7961 0.02310 0.01586 -0.0462 1.0000 0.0407
-8.750 -0.7689 0.02224 0.01496 -0.0467 1.0000 0.0422
-8.500 -0.7411 0.02142 0.01405 -0.0472 1.0000 0.0440
-8.250 -0.7129 0.02066 0.01313 -0.0476 1.0000 0.0460
-8.000 -0.6849 0.01979 0.01229 -0.0481 1.0000 0.0479
-7.750 -0.6563 0.01910 0.01155 -0.0486 1.0000 0.0501
-7.500 -0.6274 0.01845 0.01080 -0.0491 1.0000 0.0526
-7.250 -0.5984 0.01772 0.01007 -0.0497 1.0000 0.0553
-7.000 -0.5692 0.01713 0.00945 -0.0502 1.0000 0.0584
-6.750 -0.5396 0.01658 0.00883 -0.0506 1.0000 0.0618
-6.500 -0.5101 0.01597 0.00824 -0.0513 1.0000 0.0660
-6.000 -0.4503 0.01495 0.00722 -0.0524 1.0000 0.0770
-5.750 -0.4203 0.01448 0.00677 -0.0529 1.0000 0.0846
-5.500 -0.3902 0.01406 0.00638 -0.0535 1.0000 0.0945
-5.250 -0.3600 0.01366 0.00603 -0.0540 1.0000 0.1070
-5.000 -0.3298 0.01331 0.00572 -0.0546 1.0000 0.1209
-4.750 -0.2955 0.01305 0.00549 -0.0560 0.9589 0.1360
-4.500 -0.2635 0.01287 0.00531 -0.0567 0.9225 0.1508
-4.000 -0.2089 0.01265 0.00502 -0.0557 0.8639 0.1806
-3.750 -0.1821 0.01254 0.00486 -0.0551 0.8388 0.1956
-3.500 -0.1546 0.01242 0.00471 -0.0547 0.8148 0.2113
-3.250 -0.1270 0.01231 0.00457 -0.0544 0.7919 0.2287
-3.000 -0.0989 0.01222 0.00445 -0.0541 0.7709 0.2483
-2.750 -0.0703 0.01213 0.00434 -0.0540 0.7509 0.2700
-2.500 -0.0415 0.01207 0.00424 -0.0539 0.7315 0.2904
-2.250 -0.0125 0.01202 0.00414 -0.0539 0.7119 0.3086
-2.000 0.0165 0.01198 0.00406 -0.0539 0.6929 0.3262
-1.750 0.0457 0.01195 0.00398 -0.0539 0.6746 0.3429
-1.500 0.0750 0.01193 0.00392 -0.0539 0.6567 0.3602
-1.250 0.1043 0.01192 0.00387 -0.0539 0.6400 0.3776
-1.000 0.1337 0.01191 0.00383 -0.0540 0.6247 0.3940
-0.750 0.1631 0.01191 0.00380 -0.0541 0.6101 0.4107
-0.500 0.1926 0.01191 0.00379 -0.0542 0.5963 0.4288
-0.250 0.2222 0.01190 0.00381 -0.0543 0.5832 0.4490
0.000 0.2516 0.01190 0.00383 -0.0544 0.5707 0.4687
0.250 0.2810 0.01192 0.00385 -0.0545 0.5581 0.4884
0.500 0.3104 0.01193 0.00388 -0.0546 0.5451 0.5094
0.750 0.3399 0.01194 0.00393 -0.0547 0.5326 0.5307
1.000 0.3692 0.01196 0.00398 -0.0548 0.5206 0.5524
1.250 0.3982 0.01198 0.00404 -0.0548 0.5082 0.5786
1.500 0.4271 0.01197 0.00412 -0.0547 0.4950 0.6117
1.750 0.4557 0.01194 0.00421 -0.0546 0.4814 0.6525
2.000 0.4836 0.01190 0.00430 -0.0543 0.4678 0.7014
2.250 0.5099 0.01182 0.00439 -0.0536 0.4548 0.7620
2.500 0.5321 0.01163 0.00438 -0.0518 0.4427 0.8556
2.750 0.5586 0.01147 0.00428 -0.0511 0.4299 1.0000
3.000 0.5884 0.01166 0.00441 -0.0513 0.4174 1.0000
3.250 0.6180 0.01186 0.00453 -0.0516 0.4048 1.0000
3.500 0.6475 0.01206 0.00468 -0.0518 0.3920 1.0000
3.750 0.6770 0.01227 0.00485 -0.0520 0.3789 1.0000
4.000 0.7063 0.01248 0.00502 -0.0522 0.3660 1.0000
4.250 0.7355 0.01272 0.00521 -0.0523 0.3528 1.0000
4.500 0.7646 0.01297 0.00542 -0.0525 0.3395 1.0000
5.000 0.8223 0.01351 0.00588 -0.0528 0.3100 1.0000
5.250 0.8510 0.01381 0.00614 -0.0529 0.2933 1.0000
5.500 0.8794 0.01415 0.00641 -0.0531 0.2753 1.0000
5.750 0.9076 0.01451 0.00672 -0.0532 0.2569 1.0000
6.000 0.9357 0.01488 0.00705 -0.0533 0.2374 1.0000
6.250 0.9635 0.01530 0.00740 -0.0534 0.2173 1.0000
6.500 0.9910 0.01578 0.00779 -0.0535 0.1984 1.0000
6.750 1.0183 0.01627 0.00823 -0.0535 0.1807 1.0000
7.000 1.0453 0.01679 0.00870 -0.0536 0.1643 1.0000
7.250 1.0720 0.01734 0.00922 -0.0536 0.1487 1.0000
7.500 1.0984 0.01792 0.00976 -0.0536 0.1339 1.0000
7.750 1.1245 0.01854 0.01033 -0.0535 0.1190 1.0000
8.000 1.1501 0.01920 0.01096 -0.0534 0.1050 1.0000
8.250 1.1752 0.01991 0.01163 -0.0533 0.0922 1.0000
8.500 1.1998 0.02066 0.01236 -0.0531 0.0813 1.0000
8.750 1.2239 0.02145 0.01315 -0.0529 0.0726 1.0000
9.000 1.2473 0.02229 0.01399 -0.0526 0.0657 1.0000
9.250 1.2700 0.02317 0.01488 -0.0522 0.0601 1.0000
9.500 1.2924 0.02404 0.01581 -0.0517 0.0558 1.0000
9.750 1.3136 0.02500 0.01681 -0.0512 0.0522 1.0000
10.000 1.3340 0.02599 0.01787 -0.0506 0.0492 1.0000
10.250 1.3538 0.02698 0.01894 -0.0499 0.0465 1.0000
10.500 1.3711 0.02816 0.02016 -0.0490 0.0444 1.0000
10.750 1.3877 0.02933 0.02143 -0.0481 0.0426 1.0000
11.000 1.4034 0.03051 0.02271 -0.0470 0.0409 1.0000
11.250 1.4169 0.03179 0.02407 -0.0458 0.0394 1.0000
11.500 1.4260 0.03329 0.02564 -0.0444 0.0381 1.0000
11.750 1.4312 0.03493 0.02737 -0.0425 0.0372 1.0000
12.000 1.4346 0.03667 0.02926 -0.0408 0.0363 1.0000
12.250 1.4375 0.03878 0.03149 -0.0398 0.0354 1.0000
12.500 1.4399 0.04119 0.03403 -0.0394 0.0347 1.0000
12.750 1.4418 0.04387 0.03682 -0.0394 0.0340 1.0000
13.000 1.4426 0.04682 0.03988 -0.0398 0.0334 1.0000
13.250 1.4420 0.05008 0.04322 -0.0404 0.0328 1.0000
13.500 1.4395 0.05361 0.04683 -0.0411 0.0323 1.0000
13.750 1.4380 0.05714 0.05049 -0.0419 0.0318 1.0000
14.000 1.4360 0.06079 0.05430 -0.0428 0.0313 1.0000
14.250 1.4328 0.06466 0.05832 -0.0439 0.0307 1.0000
14.500 1.4286 0.06871 0.06251 -0.0451 0.0302 1.0000
14.750 1.4234 0.07293 0.06686 -0.0464 0.0298 1.0000
15.000 1.4175 0.07730 0.07135 -0.0478 0.0293 1.0000
15.250 1.4109 0.08179 0.07595 -0.0494 0.0290 1.0000
15.500 1.4041 0.08637 0.08064 -0.0510 0.0286 1.0000
15.750 1.3977 0.09106 0.08543 -0.0528 0.0283 1.0000
16.000 1.3916 0.09577 0.09023 -0.0546 0.0280 1.0000
16.250 1.3859 0.10044 0.09498 -0.0564 0.0277 1.0000
16.500 1.3813 0.10493 0.09954 -0.0581 0.0275 1.0000
16.750 1.3728 0.11043 0.10518 -0.0606 0.0272 1.0000
17.000 1.3623 0.11648 0.11142 -0.0636 0.0270 1.0000
17.250 1.3508 0.12291 0.11803 -0.0670 0.0268 1.0000
17.500 1.3382 0.12977 0.12507 -0.0708 0.0265 1.0000
17.750 1.3239 0.13722 0.13270 -0.0752 0.0263 1.0000
18.000 1.3071 0.14549 0.14116 -0.0802 0.0261 1.0000
18.250 1.2863 0.15515 0.15103 -0.0865 0.0259 1.0000
18.500 1.2499 0.16967 0.16582 -0.0964 0.0259 1.0000
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