OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF117 AIRFOIL (oaf117-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.71 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf117-il-1000000-n5.txt Download as CSV file: xf-oaf117-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.2997 0.07607 0.07291 -0.0002 1.0000 0.0123
-16.000 -1.3692 0.06130 0.05792 -0.0096 1.0000 0.0122
-15.750 -1.4288 0.04765 0.04403 -0.0195 1.0000 0.0120
-15.500 -1.4612 0.03535 0.03143 -0.0338 1.0000 0.0120
-15.250 -1.4512 0.03188 0.02778 -0.0379 1.0000 0.0121
-15.000 -1.4359 0.02992 0.02569 -0.0392 1.0000 0.0123
-14.750 -1.4191 0.02807 0.02373 -0.0403 1.0000 0.0126
-14.500 -1.3994 0.02664 0.02222 -0.0409 1.0000 0.0129
-14.250 -1.3780 0.02544 0.02094 -0.0414 1.0000 0.0133
-14.000 -1.3553 0.02439 0.01982 -0.0418 1.0000 0.0136
-13.750 -1.3316 0.02344 0.01879 -0.0422 1.0000 0.0140
-13.500 -1.3072 0.02258 0.01786 -0.0425 1.0000 0.0143
-13.250 -1.2821 0.02180 0.01701 -0.0428 1.0000 0.0147
-13.000 -1.2566 0.02105 0.01619 -0.0431 1.0000 0.0151
-12.750 -1.2310 0.02023 0.01531 -0.0434 1.0000 0.0156
-12.500 -1.2047 0.01953 0.01457 -0.0437 1.0000 0.0161
-12.250 -1.1780 0.01889 0.01388 -0.0440 1.0000 0.0166
-12.000 -1.1509 0.01830 0.01324 -0.0443 1.0000 0.0171
-11.750 -1.1235 0.01775 0.01263 -0.0446 1.0000 0.0176
-11.500 -1.0958 0.01724 0.01206 -0.0448 1.0000 0.0179
-11.250 -1.0681 0.01665 0.01143 -0.0452 1.0000 0.0186
-11.000 -1.0401 0.01614 0.01090 -0.0455 1.0000 0.0193
-10.750 -1.0119 0.01568 0.01041 -0.0458 1.0000 0.0200
-10.500 -0.9834 0.01526 0.00995 -0.0460 1.0000 0.0207
-10.250 -0.9548 0.01487 0.00951 -0.0463 1.0000 0.0213
-10.000 -0.9261 0.01440 0.00902 -0.0466 1.0000 0.0221
-9.750 -0.8973 0.01399 0.00860 -0.0469 1.0000 0.0230
-9.500 -0.8683 0.01363 0.00822 -0.0472 1.0000 0.0239
-9.250 -0.8391 0.01329 0.00785 -0.0475 1.0000 0.0247
-9.000 -0.8099 0.01294 0.00747 -0.0478 1.0000 0.0255
-8.750 -0.7806 0.01258 0.00710 -0.0481 1.0000 0.0266
-8.500 -0.7511 0.01226 0.00677 -0.0484 1.0000 0.0278
-8.250 -0.7216 0.01198 0.00647 -0.0487 1.0000 0.0289
-8.000 -0.6920 0.01168 0.00615 -0.0490 1.0000 0.0299
-7.750 -0.6617 0.01140 0.00587 -0.0495 0.9747 0.0313
-7.500 -0.6353 0.01132 0.00570 -0.0489 0.9237 0.0327
-7.250 -0.6087 0.01121 0.00549 -0.0484 0.8926 0.0340
-7.000 -0.5807 0.01104 0.00523 -0.0482 0.8658 0.0357
-6.750 -0.5522 0.01088 0.00499 -0.0482 0.8411 0.0375
-6.500 -0.5232 0.01075 0.00476 -0.0482 0.8180 0.0393
-6.250 -0.4939 0.01059 0.00453 -0.0483 0.7954 0.0415
-6.000 -0.4644 0.01044 0.00431 -0.0485 0.7728 0.0440
-5.750 -0.4349 0.01034 0.00410 -0.0487 0.7507 0.0461
-5.500 -0.4052 0.01018 0.00389 -0.0489 0.7289 0.0498
-5.250 -0.3754 0.01006 0.00371 -0.0491 0.7092 0.0533
-5.000 -0.3456 0.00991 0.00352 -0.0494 0.6899 0.0583
-4.750 -0.3157 0.00979 0.00335 -0.0496 0.6705 0.0640
-4.500 -0.2857 0.00965 0.00317 -0.0499 0.6513 0.0723
-4.250 -0.2557 0.00950 0.00302 -0.0502 0.6345 0.0832
-4.000 -0.2257 0.00935 0.00288 -0.0506 0.6204 0.0969
-3.750 -0.1956 0.00922 0.00276 -0.0509 0.6065 0.1105
-3.500 -0.1657 0.00915 0.00266 -0.0511 0.5919 0.1199
-3.250 -0.1357 0.00907 0.00255 -0.0514 0.5774 0.1299
-3.000 -0.1057 0.00899 0.00246 -0.0516 0.5630 0.1386
-2.750 -0.0757 0.00892 0.00238 -0.0518 0.5504 0.1488
-2.500 -0.0456 0.00883 0.00231 -0.0521 0.5397 0.1640
-2.250 -0.0156 0.00877 0.00225 -0.0524 0.5287 0.1776
-2.000 0.0144 0.00870 0.00220 -0.0526 0.5189 0.1904
-1.750 0.0444 0.00864 0.00215 -0.0529 0.5085 0.2044
-1.500 0.0745 0.00854 0.00211 -0.0532 0.4979 0.2286
-1.250 0.1046 0.00848 0.00208 -0.0534 0.4870 0.2488
-1.000 0.1345 0.00846 0.00206 -0.0537 0.4765 0.2627
-0.750 0.1645 0.00843 0.00204 -0.0539 0.4674 0.2785
-0.500 0.1944 0.00843 0.00204 -0.0541 0.4569 0.2924
-0.250 0.2243 0.00842 0.00204 -0.0543 0.4457 0.3056
0.000 0.2542 0.00843 0.00205 -0.0545 0.4345 0.3188
0.250 0.2841 0.00845 0.00206 -0.0548 0.4205 0.3336
0.500 0.3140 0.00849 0.00208 -0.0550 0.4061 0.3477
0.750 0.3438 0.00852 0.00211 -0.0552 0.3937 0.3631
1.000 0.3736 0.00856 0.00215 -0.0554 0.3827 0.3762
1.250 0.4034 0.00860 0.00219 -0.0556 0.3712 0.3896
1.500 0.4332 0.00864 0.00224 -0.0558 0.3601 0.4047
1.750 0.4630 0.00869 0.00229 -0.0560 0.3488 0.4188
2.000 0.4927 0.00876 0.00235 -0.0562 0.3383 0.4317
2.250 0.5224 0.00882 0.00243 -0.0564 0.3267 0.4485
2.500 0.5521 0.00887 0.00251 -0.0566 0.3153 0.4687
2.750 0.5817 0.00894 0.00259 -0.0568 0.3045 0.4869
3.000 0.6113 0.00904 0.00269 -0.0570 0.2911 0.5037
3.250 0.6409 0.00913 0.00279 -0.0572 0.2792 0.5249
3.500 0.6705 0.00922 0.00291 -0.0575 0.2683 0.5482
3.750 0.7000 0.00931 0.00304 -0.0577 0.2570 0.5766
4.000 0.7294 0.00941 0.00318 -0.0579 0.2413 0.6125
4.250 0.7588 0.00957 0.00336 -0.0582 0.2173 0.6575
4.500 0.7879 0.00971 0.00356 -0.0585 0.1961 0.7171
4.750 0.8166 0.00980 0.00377 -0.0586 0.1784 0.7880
5.000 0.8409 0.00970 0.00394 -0.0576 0.1650 0.9096
5.250 0.8671 0.00978 0.00403 -0.0571 0.1522 1.0000
5.500 0.8960 0.01006 0.00424 -0.0572 0.1395 1.0000
5.750 0.9249 0.01036 0.00446 -0.0574 0.1269 1.0000
6.000 0.9536 0.01066 0.00469 -0.0576 0.1145 1.0000
6.250 0.9823 0.01095 0.00493 -0.0577 0.1034 1.0000
6.500 1.0107 0.01130 0.00521 -0.0579 0.0907 1.0000
6.750 1.0389 0.01168 0.00550 -0.0580 0.0786 1.0000
7.000 1.0671 0.01204 0.00580 -0.0581 0.0688 1.0000
7.250 1.0951 0.01242 0.00613 -0.0582 0.0600 1.0000
7.500 1.1230 0.01278 0.00645 -0.0582 0.0531 1.0000
7.750 1.1508 0.01314 0.00678 -0.0583 0.0479 1.0000
8.000 1.1784 0.01351 0.00713 -0.0583 0.0434 1.0000
8.250 1.2059 0.01387 0.00747 -0.0583 0.0398 1.0000
8.500 1.2333 0.01425 0.00784 -0.0583 0.0367 1.0000
8.750 1.2605 0.01461 0.00821 -0.0582 0.0343 1.0000
9.000 1.2874 0.01502 0.00860 -0.0582 0.0321 1.0000
9.250 1.3143 0.01538 0.00898 -0.0581 0.0306 1.0000
9.500 1.3408 0.01579 0.00940 -0.0580 0.0289 1.0000
9.750 1.3670 0.01624 0.00985 -0.0578 0.0273 1.0000
10.000 1.3933 0.01664 0.01027 -0.0577 0.0261 1.0000
10.250 1.4191 0.01708 0.01073 -0.0575 0.0249 1.0000
10.500 1.4444 0.01758 0.01123 -0.0572 0.0238 1.0000
10.750 1.4695 0.01807 0.01175 -0.0570 0.0229 1.0000
11.000 1.4945 0.01853 0.01225 -0.0567 0.0222 1.0000
11.250 1.5190 0.01904 0.01279 -0.0564 0.0215 1.0000
11.500 1.5429 0.01958 0.01336 -0.0560 0.0207 1.0000
11.750 1.5661 0.02019 0.01399 -0.0555 0.0200 1.0000
12.000 1.5886 0.02083 0.01467 -0.0550 0.0194 1.0000
12.250 1.6113 0.02140 0.01529 -0.0544 0.0190 1.0000
12.500 1.6331 0.02202 0.01595 -0.0538 0.0184 1.0000
12.750 1.6541 0.02269 0.01666 -0.0531 0.0179 1.0000
13.000 1.6740 0.02341 0.01744 -0.0523 0.0174 1.0000
13.250 1.6925 0.02421 0.01827 -0.0514 0.0170 1.0000
13.500 1.7091 0.02511 0.01922 -0.0503 0.0166 1.0000
13.750 1.7236 0.02609 0.02026 -0.0489 0.0162 1.0000
14.000 1.7371 0.02701 0.02125 -0.0474 0.0160 1.0000
14.250 1.7478 0.02805 0.02238 -0.0457 0.0158 1.0000
14.500 1.7513 0.02936 0.02377 -0.0432 0.0156 1.0000
14.750 1.7544 0.03104 0.02555 -0.0416 0.0154 1.0000
15.000 1.7579 0.03306 0.02766 -0.0408 0.0152 1.0000
15.250 1.7608 0.03542 0.03011 -0.0405 0.0150 1.0000
15.500 1.7626 0.03814 0.03293 -0.0408 0.0148 1.0000
15.750 1.7627 0.04124 0.03613 -0.0413 0.0146 1.0000
16.000 1.7608 0.04475 0.03974 -0.0422 0.0144 1.0000
16.250 1.7563 0.04869 0.04379 -0.0433 0.0142 1.0000
16.500 1.7486 0.05314 0.04834 -0.0447 0.0141 1.0000
16.750 1.7377 0.05809 0.05341 -0.0463 0.0140 1.0000
17.000 1.7234 0.06354 0.05898 -0.0481 0.0138 1.0000
17.250 1.7063 0.06947 0.06504 -0.0501 0.0138 1.0000
17.500 1.6862 0.07588 0.07158 -0.0523 0.0137 1.0000
17.750 1.6646 0.08274 0.07857 -0.0549 0.0136 1.0000
18.000 1.6424 0.08988 0.08584 -0.0577 0.0136 1.0000
18.250 1.6198 0.09731 0.09339 -0.0608 0.0135 1.0000
18.500 1.5965 0.10499 0.10120 -0.0641 0.0134 1.0000
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