OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF117 AIRFOIL (oaf117-il) Reynolds number: 500,000 Max Cl/Cd: 78.47 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf117-il-500000-n5.txt Download as CSV file: xf-oaf117-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.1456 0.08435 0.08088 0.0055 1.0000 0.0171
-15.000 -1.1751 0.07566 0.07207 0.0003 1.0000 0.0171
-14.750 -1.2052 0.06694 0.06321 -0.0052 1.0000 0.0171
-14.500 -1.2345 0.05833 0.05445 -0.0111 1.0000 0.0171
-14.250 -1.2605 0.04994 0.04591 -0.0173 1.0000 0.0171
-14.000 -1.2812 0.04171 0.03748 -0.0250 1.0000 0.0171
-13.750 -1.2764 0.03516 0.03066 -0.0349 1.0000 0.0174
-13.500 -1.2625 0.03259 0.02790 -0.0372 1.0000 0.0177
-13.250 -1.2452 0.03063 0.02579 -0.0386 1.0000 0.0180
-13.000 -1.2265 0.02882 0.02387 -0.0399 1.0000 0.0184
-12.750 -1.2052 0.02743 0.02240 -0.0407 1.0000 0.0189
-12.500 -1.1822 0.02627 0.02114 -0.0413 1.0000 0.0194
-12.250 -1.1583 0.02523 0.02000 -0.0418 1.0000 0.0200
-12.000 -1.1337 0.02426 0.01892 -0.0423 1.0000 0.0206
-11.750 -1.1085 0.02337 0.01791 -0.0427 1.0000 0.0212
-11.500 -1.0832 0.02236 0.01683 -0.0432 1.0000 0.0219
-11.250 -1.0570 0.02153 0.01595 -0.0437 1.0000 0.0225
-11.000 -1.0303 0.02080 0.01515 -0.0441 1.0000 0.0232
-10.750 -1.0032 0.02012 0.01439 -0.0445 1.0000 0.0240
-10.500 -0.9758 0.01949 0.01366 -0.0448 1.0000 0.0248
-10.250 -0.9482 0.01877 0.01289 -0.0453 1.0000 0.0257
-10.000 -0.9204 0.01814 0.01222 -0.0457 1.0000 0.0265
-9.750 -0.8922 0.01758 0.01161 -0.0461 1.0000 0.0274
-9.500 -0.8637 0.01706 0.01102 -0.0464 1.0000 0.0284
-9.250 -0.8351 0.01659 0.01048 -0.0468 1.0000 0.0294
-9.000 -0.8064 0.01599 0.00987 -0.0472 1.0000 0.0306
-8.750 -0.7775 0.01552 0.00937 -0.0476 1.0000 0.0318
-8.500 -0.7483 0.01509 0.00889 -0.0480 1.0000 0.0331
-8.250 -0.7190 0.01470 0.00844 -0.0483 1.0000 0.0343
-8.000 -0.6897 0.01420 0.00794 -0.0488 1.0000 0.0359
-7.750 -0.6602 0.01381 0.00753 -0.0492 1.0000 0.0376
-7.500 -0.6306 0.01346 0.00714 -0.0495 1.0000 0.0392
-7.250 -0.6008 0.01306 0.00673 -0.0500 1.0000 0.0410
-7.000 -0.5710 0.01270 0.00637 -0.0504 1.0000 0.0432
-6.750 -0.5411 0.01239 0.00604 -0.0508 1.0000 0.0455
-6.500 -0.5110 0.01205 0.00569 -0.0512 0.9939 0.0479
-6.250 -0.4802 0.01188 0.00548 -0.0516 0.9333 0.0510
-6.000 -0.4543 0.01176 0.00526 -0.0509 0.8997 0.0541
-5.750 -0.4275 0.01158 0.00501 -0.0504 0.8724 0.0582
-5.500 -0.3997 0.01142 0.00477 -0.0502 0.8470 0.0627
-5.250 -0.3714 0.01123 0.00451 -0.0501 0.8233 0.0694
-5.000 -0.3425 0.01104 0.00427 -0.0501 0.8001 0.0780
-4.750 -0.3134 0.01086 0.00406 -0.0502 0.7773 0.0895
-4.500 -0.2841 0.01071 0.00386 -0.0503 0.7553 0.1033
-4.250 -0.2546 0.01057 0.00368 -0.0505 0.7352 0.1161
-4.000 -0.2250 0.01044 0.00352 -0.0507 0.7164 0.1279
-3.750 -0.1953 0.01034 0.00336 -0.0509 0.6965 0.1384
-3.500 -0.1655 0.01024 0.00322 -0.0511 0.6764 0.1499
-3.250 -0.1357 0.01014 0.00310 -0.0513 0.6582 0.1646
-3.000 -0.1059 0.01006 0.00299 -0.0516 0.6434 0.1787
-2.750 -0.0760 0.00999 0.00289 -0.0518 0.6281 0.1923
-2.500 -0.0461 0.00991 0.00279 -0.0520 0.6113 0.2069
-2.250 -0.0162 0.00984 0.00272 -0.0523 0.5947 0.2246
-2.000 0.0138 0.00973 0.00266 -0.0526 0.5811 0.2485
-1.750 0.0438 0.00966 0.00261 -0.0529 0.5691 0.2699
-1.500 0.0737 0.00962 0.00257 -0.0531 0.5576 0.2857
-1.250 0.1037 0.00959 0.00254 -0.0533 0.5458 0.3022
-1.000 0.1336 0.00956 0.00252 -0.0535 0.5348 0.3169
-0.750 0.1634 0.00956 0.00250 -0.0537 0.5233 0.3307
-0.500 0.1933 0.00955 0.00249 -0.0539 0.5112 0.3463
-0.250 0.2232 0.00955 0.00250 -0.0541 0.5004 0.3616
0.000 0.2530 0.00957 0.00250 -0.0543 0.4898 0.3758
0.250 0.2828 0.00957 0.00252 -0.0545 0.4781 0.3915
0.500 0.3127 0.00958 0.00255 -0.0547 0.4665 0.4088
0.750 0.3424 0.00962 0.00259 -0.0549 0.4539 0.4253
1.000 0.3722 0.00966 0.00262 -0.0551 0.4398 0.4409
1.250 0.4019 0.00971 0.00267 -0.0553 0.4260 0.4559
1.500 0.4316 0.00975 0.00273 -0.0555 0.4138 0.4750
1.750 0.4613 0.00979 0.00280 -0.0557 0.4020 0.4955
2.000 0.4910 0.00985 0.00287 -0.0559 0.3902 0.5155
2.250 0.5206 0.00990 0.00295 -0.0561 0.3784 0.5362
2.500 0.5502 0.00995 0.00305 -0.0563 0.3667 0.5598
2.750 0.5797 0.00999 0.00316 -0.0565 0.3553 0.5911
3.000 0.6092 0.01002 0.00328 -0.0567 0.3428 0.6323
3.250 0.6385 0.01002 0.00342 -0.0569 0.3311 0.6830
3.500 0.6672 0.01001 0.00357 -0.0569 0.3193 0.7439
3.750 0.6940 0.00994 0.00371 -0.0564 0.3069 0.8253
4.000 0.7156 0.00968 0.00364 -0.0545 0.2943 1.0000
4.250 0.7450 0.00989 0.00380 -0.0548 0.2799 1.0000
4.500 0.7742 0.01014 0.00397 -0.0550 0.2647 1.0000
4.750 0.8034 0.01041 0.00415 -0.0552 0.2469 1.0000
5.000 0.8324 0.01070 0.00436 -0.0554 0.2269 1.0000
5.250 0.8612 0.01102 0.00457 -0.0556 0.2064 1.0000
5.500 0.8899 0.01137 0.00482 -0.0558 0.1874 1.0000
5.750 0.9185 0.01172 0.00510 -0.0560 0.1714 1.0000
6.000 0.9470 0.01207 0.00538 -0.0561 0.1570 1.0000
6.250 0.9754 0.01243 0.00567 -0.0563 0.1433 1.0000
6.500 1.0036 0.01280 0.00599 -0.0564 0.1301 1.0000
6.750 1.0316 0.01319 0.00632 -0.0565 0.1169 1.0000
7.000 1.0594 0.01361 0.00667 -0.0566 0.1040 1.0000
7.250 1.0869 0.01406 0.00706 -0.0566 0.0912 1.0000
7.500 1.1142 0.01455 0.00748 -0.0567 0.0789 1.0000
7.750 1.1413 0.01504 0.00791 -0.0567 0.0690 1.0000
8.000 1.1682 0.01552 0.00837 -0.0567 0.0610 1.0000
8.250 1.1949 0.01601 0.00884 -0.0566 0.0546 1.0000
8.500 1.2213 0.01652 0.00933 -0.0566 0.0494 1.0000
8.750 1.2476 0.01703 0.00985 -0.0565 0.0453 1.0000
9.000 1.2736 0.01754 0.01037 -0.0563 0.0421 1.0000
9.250 1.2992 0.01808 0.01092 -0.0561 0.0391 1.0000
9.500 1.3245 0.01864 0.01150 -0.0559 0.0368 1.0000
9.750 1.3497 0.01918 0.01208 -0.0557 0.0347 1.0000
10.000 1.3740 0.01980 0.01272 -0.0554 0.0329 1.0000
10.250 1.3981 0.02044 0.01340 -0.0550 0.0315 1.0000
10.500 1.4219 0.02104 0.01405 -0.0546 0.0302 1.0000
10.750 1.4450 0.02170 0.01476 -0.0542 0.0289 1.0000
11.000 1.4668 0.02249 0.01557 -0.0537 0.0277 1.0000
11.250 1.4885 0.02322 0.01637 -0.0531 0.0268 1.0000
11.500 1.5098 0.02395 0.01717 -0.0524 0.0259 1.0000
11.750 1.5298 0.02475 0.01803 -0.0517 0.0250 1.0000
12.000 1.5483 0.02564 0.01898 -0.0508 0.0243 1.0000
12.250 1.5648 0.02667 0.02006 -0.0498 0.0236 1.0000
12.500 1.5790 0.02780 0.02126 -0.0485 0.0231 1.0000
12.750 1.5925 0.02885 0.02241 -0.0471 0.0226 1.0000
13.000 1.6027 0.03004 0.02370 -0.0455 0.0221 1.0000
13.250 1.6067 0.03146 0.02522 -0.0433 0.0217 1.0000
13.500 1.6096 0.03328 0.02715 -0.0419 0.0214 1.0000
13.750 1.6127 0.03545 0.02942 -0.0413 0.0210 1.0000
14.000 1.6149 0.03800 0.03208 -0.0412 0.0206 1.0000
14.250 1.6156 0.04099 0.03517 -0.0417 0.0203 1.0000
14.500 1.6138 0.04449 0.03877 -0.0426 0.0200 1.0000
14.750 1.6088 0.04857 0.04297 -0.0438 0.0197 1.0000
15.000 1.6008 0.05314 0.04766 -0.0454 0.0195 1.0000
15.250 1.5948 0.05750 0.05215 -0.0468 0.0193 1.0000
15.500 1.5861 0.06226 0.05704 -0.0483 0.0192 1.0000
15.750 1.5758 0.06727 0.06219 -0.0500 0.0190 1.0000
16.000 1.5635 0.07263 0.06767 -0.0519 0.0189 1.0000
16.250 1.5500 0.07820 0.07337 -0.0538 0.0188 1.0000
16.500 1.5359 0.08396 0.07927 -0.0560 0.0187 1.0000
16.750 1.5222 0.08984 0.08526 -0.0582 0.0185 1.0000
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