OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF128 AIRFOIL (oaf128-il) Reynolds number: 500,000 Max Cl/Cd: 70.96 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf128-il-500000-n5.txt Download as CSV file: xf-oaf128-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF128 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
------ -------- --------- --------- -------- -------- --------
-15.750 -1.2428 0.08353 0.07932 0.0153 1.0000 0.0175
-15.500 -1.2591 0.07727 0.07295 0.0121 1.0000 0.0175
-15.250 -1.2751 0.07111 0.06668 0.0088 1.0000 0.0176
-15.000 -1.2908 0.06501 0.06046 0.0055 1.0000 0.0177
-14.750 -1.3050 0.05912 0.05445 0.0022 1.0000 0.0177
-14.500 -1.3169 0.05346 0.04866 -0.0012 1.0000 0.0178
-14.250 -1.3259 0.04809 0.04316 -0.0047 1.0000 0.0179
-14.000 -1.3312 0.04306 0.03799 -0.0084 1.0000 0.0180
-13.750 -1.3336 0.03845 0.03323 -0.0123 1.0000 0.0181
-13.500 -1.3368 0.03453 0.02915 -0.0154 1.0000 0.0182
-13.250 -1.3281 0.03225 0.02673 -0.0166 1.0000 0.0184
-13.000 -1.3141 0.03057 0.02492 -0.0169 1.0000 0.0186
-12.750 -1.2974 0.02912 0.02337 -0.0172 1.0000 0.0188
-12.500 -1.2804 0.02757 0.02175 -0.0174 1.0000 0.0191
-12.250 -1.2605 0.02633 0.02043 -0.0176 1.0000 0.0194
-12.000 -1.2386 0.02526 0.01930 -0.0178 1.0000 0.0198
-11.750 -1.2156 0.02430 0.01828 -0.0180 1.0000 0.0201
-11.500 -1.1917 0.02341 0.01732 -0.0182 1.0000 0.0205
-11.250 -1.1671 0.02258 0.01642 -0.0183 1.0000 0.0210
-11.000 -1.1417 0.02181 0.01558 -0.0185 1.0000 0.0215
-10.750 -1.1157 0.02111 0.01481 -0.0187 1.0000 0.0219
-10.500 -1.0899 0.02027 0.01392 -0.0190 1.0000 0.0225
-10.250 -1.0633 0.01956 0.01318 -0.0193 1.0000 0.0231
-10.000 -1.0362 0.01893 0.01251 -0.0196 1.0000 0.0238
-9.750 -1.0087 0.01833 0.01186 -0.0199 1.0000 0.0245
-9.500 -0.9808 0.01778 0.01125 -0.0202 1.0000 0.0252
-9.250 -0.9528 0.01718 0.01062 -0.0205 1.0000 0.0260
-9.000 -0.9245 0.01661 0.01003 -0.0208 1.0000 0.0269
-8.750 -0.8959 0.01611 0.00951 -0.0212 1.0000 0.0279
-8.500 -0.8670 0.01567 0.00903 -0.0215 1.0000 0.0291
-8.250 -0.8381 0.01517 0.00851 -0.0219 1.0000 0.0306
-8.000 -0.8089 0.01472 0.00806 -0.0223 1.0000 0.0324
-7.750 -0.7795 0.01430 0.00763 -0.0226 1.0000 0.0343
-7.500 -0.7500 0.01387 0.00720 -0.0230 1.0000 0.0369
-7.250 -0.7203 0.01346 0.00679 -0.0235 1.0000 0.0401
-7.000 -0.6905 0.01305 0.00640 -0.0239 1.0000 0.0449
-6.750 -0.6605 0.01262 0.00602 -0.0244 1.0000 0.0523
-6.500 -0.6304 0.01233 0.00577 -0.0248 0.9410 0.0631
-6.250 -0.6049 0.01212 0.00555 -0.0241 0.9051 0.0748
-6.000 -0.5783 0.01192 0.00533 -0.0237 0.8773 0.0863
-5.750 -0.5507 0.01173 0.00510 -0.0234 0.8522 0.0969
-5.500 -0.5223 0.01154 0.00487 -0.0233 0.8277 0.1064
-5.250 -0.4936 0.01138 0.00465 -0.0233 0.8031 0.1152
-5.000 -0.4645 0.01124 0.00444 -0.0233 0.7788 0.1245
-4.750 -0.4351 0.01107 0.00423 -0.0235 0.7548 0.1358
-4.500 -0.4055 0.01090 0.00404 -0.0237 0.7301 0.1496
-4.250 -0.3757 0.01076 0.00387 -0.0239 0.7058 0.1662
-4.000 -0.3458 0.01060 0.00371 -0.0242 0.6836 0.1872
-3.750 -0.3158 0.01046 0.00356 -0.0245 0.6632 0.2042
-3.500 -0.2857 0.01037 0.00342 -0.0248 0.6438 0.2154
-3.250 -0.2555 0.01028 0.00329 -0.0251 0.6249 0.2268
-3.000 -0.2253 0.01018 0.00318 -0.0254 0.6077 0.2417
-2.750 -0.1951 0.01009 0.00309 -0.0257 0.5925 0.2578
-2.500 -0.1648 0.01002 0.00301 -0.0260 0.5785 0.2728
-2.250 -0.1346 0.00996 0.00294 -0.0263 0.5634 0.2884
-2.000 -0.1043 0.00993 0.00288 -0.0265 0.5459 0.3026
-1.750 -0.0741 0.00992 0.00282 -0.0268 0.5294 0.3159
-1.500 -0.0439 0.00989 0.00278 -0.0271 0.5152 0.3300
-1.250 -0.0136 0.00986 0.00275 -0.0273 0.5015 0.3427
-1.000 0.0166 0.00986 0.00273 -0.0276 0.4890 0.3549
-0.500 0.0771 0.00983 0.00271 -0.0281 0.4670 0.3854
-0.250 0.1074 0.00982 0.00271 -0.0284 0.4572 0.3998
0.000 0.1376 0.00982 0.00272 -0.0286 0.4470 0.4108
0.250 0.1678 0.00984 0.00273 -0.0289 0.4365 0.4227
0.500 0.1980 0.00985 0.00274 -0.0291 0.4260 0.4338
0.750 0.2282 0.00988 0.00277 -0.0293 0.4172 0.4444
1.000 0.2584 0.00990 0.00280 -0.0296 0.4073 0.4569
1.250 0.2886 0.00993 0.00284 -0.0298 0.3975 0.4686
1.750 0.3489 0.01000 0.00294 -0.0303 0.3776 0.4965
2.000 0.3790 0.01005 0.00301 -0.0306 0.3661 0.5122
2.250 0.4090 0.01013 0.00307 -0.0309 0.3480 0.5294
2.500 0.4390 0.01022 0.00315 -0.0311 0.3271 0.5484
2.750 0.4690 0.01030 0.00325 -0.0314 0.3109 0.5700
3.000 0.4990 0.01039 0.00335 -0.0317 0.2964 0.5927
3.250 0.5289 0.01048 0.00347 -0.0320 0.2814 0.6186
3.500 0.5587 0.01056 0.00361 -0.0322 0.2660 0.6516
3.750 0.5883 0.01065 0.00377 -0.0324 0.2505 0.6901
4.000 0.6176 0.01073 0.00394 -0.0326 0.2366 0.7312
4.250 0.6464 0.01083 0.00412 -0.0326 0.2239 0.7717
4.500 0.6746 0.01094 0.00431 -0.0324 0.2125 0.8112
4.750 0.7018 0.01106 0.00449 -0.0321 0.2006 0.8514
5.000 0.7274 0.01113 0.00463 -0.0313 0.1882 0.8948
5.250 0.7515 0.01109 0.00464 -0.0301 0.1750 1.0000
5.500 0.7810 0.01142 0.00487 -0.0305 0.1575 1.0000
5.750 0.8104 0.01179 0.00513 -0.0308 0.1389 1.0000
6.000 0.8397 0.01217 0.00542 -0.0311 0.1235 1.0000
6.250 0.8688 0.01255 0.00573 -0.0314 0.1116 1.0000
6.500 0.8978 0.01293 0.00605 -0.0317 0.1024 1.0000
6.750 0.9268 0.01327 0.00636 -0.0319 0.0955 1.0000
7.000 0.9556 0.01363 0.00669 -0.0321 0.0901 1.0000
7.250 0.9843 0.01398 0.00703 -0.0323 0.0850 1.0000
7.500 1.0128 0.01436 0.00739 -0.0325 0.0810 1.0000
7.750 1.0413 0.01470 0.00774 -0.0326 0.0775 1.0000
8.000 1.0693 0.01512 0.00813 -0.0328 0.0739 1.0000
8.250 1.0975 0.01548 0.00852 -0.0329 0.0712 1.0000
8.500 1.1254 0.01586 0.00891 -0.0330 0.0686 1.0000
8.750 1.1528 0.01631 0.00935 -0.0331 0.0659 1.0000
9.000 1.1803 0.01672 0.00979 -0.0331 0.0637 1.0000
9.250 1.2075 0.01713 0.01022 -0.0331 0.0616 1.0000
9.500 1.2344 0.01759 0.01069 -0.0331 0.0595 1.0000
9.750 1.2607 0.01813 0.01124 -0.0331 0.0574 1.0000
10.000 1.2873 0.01855 0.01171 -0.0330 0.0558 1.0000
10.250 1.3134 0.01904 0.01223 -0.0329 0.0540 1.0000
10.500 1.3389 0.01958 0.01279 -0.0328 0.0523 1.0000
10.750 1.3637 0.02019 0.01342 -0.0326 0.0507 1.0000
11.000 1.3888 0.02070 0.01399 -0.0324 0.0493 1.0000
11.250 1.4133 0.02127 0.01461 -0.0322 0.0478 1.0000
11.500 1.4370 0.02190 0.01527 -0.0319 0.0464 1.0000
11.750 1.4594 0.02265 0.01603 -0.0316 0.0450 1.0000
12.000 1.4824 0.02327 0.01674 -0.0312 0.0439 1.0000
12.250 1.5044 0.02395 0.01748 -0.0307 0.0426 1.0000
12.500 1.5253 0.02471 0.01828 -0.0302 0.0414 1.0000
12.750 1.5444 0.02559 0.01919 -0.0295 0.0403 1.0000
13.000 1.5625 0.02650 0.02017 -0.0288 0.0393 1.0000
13.250 1.5798 0.02739 0.02115 -0.0280 0.0383 1.0000
13.500 1.5948 0.02838 0.02222 -0.0270 0.0373 1.0000
13.750 1.6066 0.02954 0.02344 -0.0258 0.0364 1.0000
14.000 1.6111 0.03105 0.02503 -0.0241 0.0357 1.0000
14.250 1.6121 0.03321 0.02727 -0.0233 0.0351 1.0000
14.500 1.6165 0.03545 0.02963 -0.0233 0.0345 1.0000
14.750 1.6205 0.03801 0.03231 -0.0239 0.0338 1.0000
15.000 1.6229 0.04096 0.03538 -0.0248 0.0331 1.0000
15.250 1.6231 0.04432 0.03885 -0.0260 0.0325 1.0000
15.500 1.6206 0.04813 0.04277 -0.0275 0.0320 1.0000
15.750 1.6151 0.05241 0.04715 -0.0292 0.0315 1.0000
16.000 1.6059 0.05720 0.05204 -0.0311 0.0311 1.0000
16.250 1.5934 0.06248 0.05744 -0.0332 0.0307 1.0000
16.500 1.5817 0.06760 0.06269 -0.0351 0.0304 1.0000
16.750 1.5691 0.07290 0.06812 -0.0371 0.0301 1.0000
17.000 1.5546 0.07849 0.07384 -0.0393 0.0297 1.0000
17.250 1.5399 0.08425 0.07972 -0.0416 0.0294 1.0000
17.500 1.5253 0.09019 0.08577 -0.0441 0.0290 1.0000
17.750 1.5104 0.09631 0.09201 -0.0467 0.0287 1.0000
18.000 1.4953 0.10261 0.09841 -0.0496 0.0283 1.0000
18.250 1.4800 0.10900 0.10491 -0.0525 0.0280 1.0000
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