OAF139 AIRFOIL (oaf139-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF139 AIRFOIL (oaf139-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.27 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf139-il-1000000-n5.txt Download as CSV file: xf-oaf139-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF139 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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.6160 0.09572 0.09160 0.0496 1.0000 0.0200
-18.500 -1.6374 0.08883 0.08460 0.0468 1.0000 0.0202
-18.250 -1.6588 0.08204 0.07768 0.0441 1.0000 0.0204
-18.000 -1.6789 0.07566 0.07119 0.0418 1.0000 0.0206
-17.750 -1.6995 0.06943 0.06484 0.0396 1.0000 0.0209
-17.500 -1.7174 0.06367 0.05896 0.0377 1.0000 0.0211
-17.250 -1.7329 0.05825 0.05343 0.0360 1.0000 0.0214
-17.000 -1.7453 0.05327 0.04834 0.0344 1.0000 0.0218
-16.750 -1.7542 0.04877 0.04373 0.0330 1.0000 0.0222
-16.500 -1.7598 0.04472 0.03956 0.0317 1.0000 0.0225
-16.250 -1.7622 0.04111 0.03586 0.0306 1.0000 0.0229
-16.000 -1.7636 0.03770 0.03234 0.0296 1.0000 0.0234
-15.750 -1.7634 0.03464 0.02920 0.0289 1.0000 0.0240
-15.500 -1.7609 0.03205 0.02654 0.0287 1.0000 0.0247
-15.250 -1.7572 0.02989 0.02430 0.0290 1.0000 0.0254
-15.000 -1.7528 0.02812 0.02245 0.0300 1.0000 0.0261
-14.750 -1.7491 0.02673 0.02098 0.0320 1.0000 0.0268
-14.500 -1.7412 0.02557 0.01977 0.0339 1.0000 0.0277
-14.250 -1.7281 0.02461 0.01876 0.0354 1.0000 0.0288
-14.000 -1.7119 0.02378 0.01790 0.0365 1.0000 0.0299
-13.750 -1.6934 0.02305 0.01712 0.0374 1.0000 0.0308
-13.500 -1.6748 0.02225 0.01629 0.0383 1.0000 0.0321
-13.250 -1.6545 0.02156 0.01558 0.0390 1.0000 0.0335
-13.000 -1.6328 0.02095 0.01494 0.0397 1.0000 0.0348
-12.750 -1.6110 0.02031 0.01427 0.0402 1.0000 0.0363
-12.500 -1.5883 0.01970 0.01366 0.0407 1.0000 0.0380
-12.250 -1.5646 0.01919 0.01311 0.0412 1.0000 0.0396
-12.000 -1.5407 0.01864 0.01256 0.0415 1.0000 0.0412
-11.750 -1.5164 0.01811 0.01202 0.0419 1.0000 0.0432
-11.500 -1.4913 0.01766 0.01155 0.0422 1.0000 0.0450
-11.250 -1.4660 0.01719 0.01107 0.0424 1.0000 0.0468
-11.000 -1.4405 0.01672 0.01060 0.0426 1.0000 0.0490
-10.750 -1.4144 0.01632 0.01018 0.0428 1.0000 0.0511
-10.500 -1.3881 0.01590 0.00976 0.0429 1.0000 0.0532
-10.250 -1.3617 0.01548 0.00934 0.0430 1.0000 0.0558
-10.000 -1.3347 0.01513 0.00898 0.0431 1.0000 0.0580
-9.750 -1.3076 0.01475 0.00861 0.0432 1.0000 0.0606
-9.500 -1.2804 0.01437 0.00824 0.0432 1.0000 0.0636
-9.250 -1.2527 0.01406 0.00792 0.0433 1.0000 0.0661
-9.000 -1.2252 0.01368 0.00757 0.0432 1.0000 0.0696
-8.750 -1.1973 0.01336 0.00725 0.0432 1.0000 0.0731
-8.500 -1.1692 0.01304 0.00695 0.0432 1.0000 0.0766
-8.250 -1.1411 0.01271 0.00664 0.0431 1.0000 0.0809
-8.000 -1.1127 0.01243 0.00636 0.0431 1.0000 0.0850
-7.750 -1.0843 0.01209 0.00607 0.0430 1.0000 0.0906
-7.500 -1.0557 0.01181 0.00581 0.0428 1.0000 0.0958
-7.250 -1.0270 0.01148 0.00553 0.0427 1.0000 0.1029
-7.000 -0.9982 0.01117 0.00527 0.0426 1.0000 0.1104
-6.750 -0.9755 0.01121 0.00516 0.0440 0.8693 0.1180
-6.500 -0.9487 0.01109 0.00490 0.0443 0.8031 0.1283
-6.250 -0.9203 0.01093 0.00465 0.0443 0.7480 0.1390
-6.000 -0.8913 0.01076 0.00442 0.0441 0.7057 0.1504
-5.750 -0.8620 0.01061 0.00420 0.0439 0.6691 0.1614
-5.500 -0.8325 0.01048 0.00402 0.0437 0.6378 0.1712
-5.250 -0.8031 0.01031 0.00384 0.0435 0.6128 0.1818
-5.000 -0.7734 0.01020 0.00368 0.0433 0.5895 0.1896
-4.750 -0.7438 0.01006 0.00353 0.0431 0.5689 0.1988
-4.500 -0.7141 0.00994 0.00338 0.0429 0.5517 0.2066
-4.250 -0.6843 0.00983 0.00325 0.0427 0.5350 0.2155
-4.000 -0.6545 0.00970 0.00311 0.0424 0.5189 0.2249
-3.500 -0.5948 0.00947 0.00288 0.0420 0.4887 0.2474
-3.250 -0.5649 0.00936 0.00277 0.0417 0.4713 0.2603
-3.000 -0.5349 0.00926 0.00268 0.0415 0.4558 0.2726
-2.750 -0.5049 0.00918 0.00260 0.0413 0.4442 0.2845
-2.500 -0.4749 0.00908 0.00252 0.0410 0.4332 0.2975
-2.250 -0.4448 0.00899 0.00245 0.0408 0.4223 0.3094
-2.000 -0.4147 0.00894 0.00239 0.0406 0.4108 0.3184
-1.750 -0.3846 0.00887 0.00234 0.0404 0.4022 0.3284
-1.500 -0.3544 0.00884 0.00229 0.0401 0.3925 0.3363
-1.250 -0.3243 0.00878 0.00225 0.0399 0.3842 0.3458
-1.000 -0.2941 0.00875 0.00221 0.0397 0.3738 0.3543
-0.750 -0.2639 0.00872 0.00219 0.0395 0.3639 0.3630
-0.500 -0.2336 0.00871 0.00216 0.0392 0.3538 0.3709
-0.250 -0.2034 0.00868 0.00214 0.0390 0.3435 0.3806
0.000 -0.1731 0.00868 0.00213 0.0388 0.3313 0.3890
0.250 -0.1428 0.00869 0.00212 0.0385 0.3177 0.3976
0.500 -0.1125 0.00871 0.00212 0.0383 0.3052 0.4054
0.750 -0.0822 0.00871 0.00213 0.0380 0.2937 0.4156
1.000 -0.0519 0.00874 0.00214 0.0378 0.2811 0.4245
1.250 -0.0215 0.00876 0.00217 0.0375 0.2690 0.4336
1.500 0.0088 0.00880 0.00219 0.0373 0.2570 0.4418
1.750 0.0391 0.00884 0.00223 0.0370 0.2453 0.4535
2.250 0.0998 0.00893 0.00232 0.0365 0.2221 0.4768
2.500 0.1302 0.00897 0.00239 0.0362 0.2123 0.4902
2.750 0.1605 0.00903 0.00245 0.0359 0.2021 0.5018
3.000 0.1908 0.00910 0.00252 0.0357 0.1941 0.5112
3.250 0.2211 0.00918 0.00260 0.0354 0.1845 0.5209
3.750 0.2817 0.00934 0.00278 0.0349 0.1670 0.5430
4.000 0.3120 0.00943 0.00288 0.0346 0.1562 0.5546
4.250 0.3423 0.00954 0.00299 0.0343 0.1462 0.5667
4.500 0.3725 0.00967 0.00311 0.0340 0.1362 0.5786
5.000 0.4329 0.00993 0.00339 0.0334 0.1191 0.6039
5.250 0.4631 0.01006 0.00355 0.0331 0.1115 0.6190
5.500 0.4932 0.01019 0.00371 0.0328 0.1050 0.6365
5.750 0.5233 0.01031 0.00388 0.0325 0.0991 0.6576
6.000 0.5533 0.01044 0.00407 0.0322 0.0931 0.6802
6.250 0.5832 0.01057 0.00425 0.0320 0.0882 0.7027
6.500 0.6130 0.01072 0.00446 0.0317 0.0825 0.7263
6.750 0.6428 0.01085 0.00466 0.0315 0.0780 0.7506
7.000 0.6723 0.01103 0.00490 0.0313 0.0728 0.7763
7.250 0.7016 0.01116 0.00512 0.0312 0.0687 0.8045
7.500 0.7306 0.01135 0.00538 0.0311 0.0641 0.8333
7.750 0.7589 0.01149 0.00562 0.0312 0.0605 0.8647
8.000 0.7862 0.01168 0.00588 0.0315 0.0564 0.8974
8.250 0.8115 0.01178 0.00609 0.0323 0.0535 0.9387
8.500 0.8402 0.01198 0.00631 0.0322 0.0501 1.0000
8.750 0.8697 0.01227 0.00660 0.0319 0.0472 1.0000
9.000 0.8991 0.01263 0.00694 0.0316 0.0441 1.0000
9.250 0.9284 0.01294 0.00726 0.0313 0.0418 1.0000
9.500 0.9575 0.01332 0.00762 0.0310 0.0395 1.0000
9.750 0.9865 0.01366 0.00798 0.0308 0.0376 1.0000
10.000 1.0153 0.01405 0.00836 0.0305 0.0356 1.0000
10.250 1.0439 0.01446 0.00877 0.0302 0.0338 1.0000
10.500 1.0725 0.01484 0.00917 0.0300 0.0325 1.0000
10.750 1.1007 0.01527 0.00961 0.0297 0.0311 1.0000
11.000 1.1287 0.01575 0.01010 0.0295 0.0298 1.0000
11.250 1.1567 0.01616 0.01055 0.0293 0.0289 1.0000
11.500 1.1844 0.01663 0.01104 0.0291 0.0278 1.0000
11.750 1.2116 0.01716 0.01158 0.0289 0.0267 1.0000
12.000 1.2386 0.01771 0.01215 0.0287 0.0257 1.0000
12.250 1.2654 0.01821 0.01270 0.0285 0.0250 1.0000
12.500 1.2919 0.01877 0.01329 0.0284 0.0243 1.0000
12.750 1.3178 0.01938 0.01393 0.0282 0.0235 1.0000
13.000 1.3431 0.02007 0.01465 0.0281 0.0229 1.0000
13.250 1.3679 0.02079 0.01542 0.0280 0.0223 1.0000
13.500 1.3926 0.02146 0.01613 0.0279 0.0218 1.0000
13.750 1.4166 0.02219 0.01691 0.0278 0.0213 1.0000
14.000 1.4397 0.02299 0.01777 0.0277 0.0209 1.0000
14.250 1.4618 0.02388 0.01871 0.0276 0.0204 1.0000
14.500 1.4826 0.02489 0.01977 0.0275 0.0199 1.0000
14.750 1.5013 0.02609 0.02103 0.0274 0.0194 1.0000
15.000 1.5184 0.02739 0.02240 0.0272 0.0190 1.0000
15.250 1.5341 0.02879 0.02389 0.0269 0.0187 1.0000
15.500 1.5445 0.03077 0.02598 0.0259 0.0185 1.0000
15.750 1.5382 0.03560 0.03098 0.0211 0.0183 1.0000
16.000 1.5305 0.04112 0.03665 0.0163 0.0182 1.0000
16.250 1.5144 0.04752 0.04320 0.0118 0.0181 1.0000
16.500 1.4895 0.05482 0.05066 0.0074 0.0180 1.0000
16.750 1.4579 0.06290 0.05889 0.0028 0.0180 1.0000
17.000 1.4216 0.07168 0.06784 -0.0020 0.0181 1.0000
17.250 1.3839 0.08080 0.07711 -0.0069 0.0181 1.0000
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