OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF128 AIRFOIL (oaf128-il) Reynolds number: 500,000 Max Cl/Cd: 74.12 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf128-il-500000.txt Download as CSV file: xf-oaf128-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.1258 0.11295 0.10971 0.0269 1.0000 0.0233
-16.250 -1.1647 0.10079 0.09730 0.0190 1.0000 0.0232
-16.000 -1.1886 0.09226 0.08859 0.0137 1.0000 0.0232
-15.750 -1.2090 0.08486 0.08104 0.0092 1.0000 0.0232
-15.500 -1.2254 0.07842 0.07446 0.0053 1.0000 0.0232
-15.250 -1.2391 0.07248 0.06838 0.0017 1.0000 0.0233
-15.000 -1.2502 0.06703 0.06280 -0.0016 1.0000 0.0234
-14.750 -1.2593 0.06191 0.05754 -0.0047 1.0000 0.0235
-14.500 -1.2654 0.05726 0.05277 -0.0076 1.0000 0.0237
-14.250 -1.2696 0.05293 0.04831 -0.0104 1.0000 0.0239
-14.000 -1.2720 0.04886 0.04411 -0.0131 1.0000 0.0240
-13.750 -1.2728 0.04510 0.04022 -0.0156 1.0000 0.0242
-13.500 -1.2726 0.04168 0.03666 -0.0177 1.0000 0.0244
-13.250 -1.2728 0.03867 0.03350 -0.0191 1.0000 0.0246
-13.000 -1.2704 0.03630 0.03098 -0.0195 1.0000 0.0248
-12.750 -1.2604 0.03442 0.02895 -0.0194 1.0000 0.0251
-12.500 -1.2464 0.03281 0.02719 -0.0194 1.0000 0.0253
-12.250 -1.2304 0.03127 0.02551 -0.0192 1.0000 0.0256
-12.000 -1.2157 0.02928 0.02349 -0.0189 1.0000 0.0260
-11.750 -1.1967 0.02791 0.02209 -0.0188 1.0000 0.0265
-11.500 -1.1757 0.02675 0.02089 -0.0188 1.0000 0.0269
-11.250 -1.1534 0.02567 0.01976 -0.0188 1.0000 0.0274
-11.000 -1.1303 0.02465 0.01866 -0.0189 1.0000 0.0280
-10.750 -1.1062 0.02369 0.01762 -0.0190 1.0000 0.0286
-10.500 -1.0812 0.02285 0.01668 -0.0191 1.0000 0.0292
-10.250 -1.0575 0.02161 0.01540 -0.0192 1.0000 0.0299
-10.000 -1.0321 0.02066 0.01445 -0.0195 1.0000 0.0308
-9.750 -1.0056 0.01992 0.01367 -0.0197 1.0000 0.0318
-9.500 -0.9784 0.01922 0.01292 -0.0200 1.0000 0.0328
-9.250 -0.9507 0.01861 0.01223 -0.0202 1.0000 0.0336
-9.000 -0.9240 0.01754 0.01116 -0.0207 1.0000 0.0350
-8.750 -0.8958 0.01689 0.01050 -0.0211 1.0000 0.0363
-8.500 -0.8672 0.01633 0.00989 -0.0214 1.0000 0.0379
-8.250 -0.8386 0.01557 0.00912 -0.0219 1.0000 0.0399
-8.000 -0.8095 0.01503 0.00857 -0.0223 1.0000 0.0423
-7.750 -0.7803 0.01440 0.00793 -0.0228 1.0000 0.0454
-7.500 -0.7507 0.01388 0.00741 -0.0232 1.0000 0.0495
-7.250 -0.7210 0.01326 0.00684 -0.0238 1.0000 0.0563
-7.000 -0.6911 0.01265 0.00632 -0.0244 1.0000 0.0695
-6.750 -0.6611 0.01213 0.00593 -0.0249 1.0000 0.0890
-6.500 -0.6310 0.01172 0.00561 -0.0255 1.0000 0.1047
-6.250 -0.6007 0.01139 0.00533 -0.0260 1.0000 0.1167
-6.000 -0.5703 0.01108 0.00506 -0.0265 1.0000 0.1278
-5.750 -0.5398 0.01078 0.00481 -0.0270 1.0000 0.1395
-5.500 -0.5091 0.01049 0.00459 -0.0275 1.0000 0.1525
-5.250 -0.4782 0.01022 0.00439 -0.0281 1.0000 0.1672
-5.000 -0.4472 0.00998 0.00422 -0.0287 1.0000 0.1825
-4.750 -0.4173 0.01002 0.00424 -0.0288 0.9365 0.1968
-4.500 -0.3928 0.00995 0.00416 -0.0277 0.9020 0.2104
-4.250 -0.3666 0.00986 0.00403 -0.0269 0.8735 0.2246
-4.000 -0.3388 0.00974 0.00392 -0.0266 0.8468 0.2445
-3.750 -0.3105 0.00964 0.00380 -0.0264 0.8209 0.2651
-3.500 -0.2816 0.00956 0.00368 -0.0263 0.7953 0.2823
-3.250 -0.2523 0.00949 0.00357 -0.0263 0.7689 0.2990
-3.000 -0.2229 0.00946 0.00347 -0.0264 0.7438 0.3158
-2.750 -0.1931 0.00942 0.00339 -0.0265 0.7203 0.3319
-2.500 -0.1632 0.00938 0.00331 -0.0266 0.6974 0.3470
-2.250 -0.1333 0.00937 0.00324 -0.0268 0.6743 0.3615
-2.000 -0.1033 0.00937 0.00318 -0.0270 0.6507 0.3748
-1.500 -0.0431 0.00939 0.00308 -0.0274 0.6103 0.4011
-1.250 -0.0129 0.00939 0.00305 -0.0276 0.5922 0.4136
-1.000 0.0173 0.00941 0.00302 -0.0278 0.5757 0.4263
-0.750 0.0475 0.00941 0.00301 -0.0280 0.5606 0.4405
-0.500 0.0777 0.00941 0.00301 -0.0283 0.5470 0.4559
-0.250 0.1079 0.00942 0.00301 -0.0285 0.5338 0.4708
0.000 0.1381 0.00942 0.00301 -0.0287 0.5210 0.4847
0.250 0.1683 0.00944 0.00302 -0.0290 0.5086 0.4996
0.500 0.1985 0.00945 0.00304 -0.0292 0.4964 0.5149
0.750 0.2288 0.00944 0.00307 -0.0295 0.4853 0.5309
1.000 0.2590 0.00946 0.00310 -0.0297 0.4744 0.5489
1.250 0.2891 0.00946 0.00314 -0.0299 0.4628 0.5688
1.500 0.3193 0.00946 0.00319 -0.0302 0.4520 0.5911
1.750 0.3494 0.00948 0.00325 -0.0304 0.4412 0.6170
2.000 0.3794 0.00945 0.00332 -0.0306 0.4296 0.6477
2.250 0.4092 0.00944 0.00339 -0.0308 0.4148 0.6829
2.500 0.4386 0.00943 0.00347 -0.0308 0.3990 0.7234
2.750 0.4675 0.00944 0.00357 -0.0308 0.3854 0.7681
3.000 0.4957 0.00940 0.00367 -0.0304 0.3727 0.8129
3.250 0.5226 0.00939 0.00375 -0.0298 0.3600 0.8584
3.500 0.5463 0.00933 0.00377 -0.0284 0.3475 0.9109
3.750 0.5716 0.00919 0.00365 -0.0275 0.3336 1.0000
4.000 0.6021 0.00936 0.00376 -0.0279 0.3190 1.0000
4.250 0.6325 0.00956 0.00389 -0.0283 0.3038 1.0000
4.500 0.6628 0.00977 0.00403 -0.0286 0.2886 1.0000
4.750 0.6929 0.00999 0.00419 -0.0290 0.2733 1.0000
5.000 0.7229 0.01024 0.00436 -0.0294 0.2574 1.0000
5.250 0.7528 0.01050 0.00455 -0.0297 0.2423 1.0000
5.500 0.7825 0.01079 0.00476 -0.0300 0.2274 1.0000
5.750 0.8121 0.01109 0.00500 -0.0303 0.2124 1.0000
6.000 0.8415 0.01141 0.00524 -0.0306 0.1964 1.0000
6.250 0.8709 0.01175 0.00551 -0.0309 0.1762 1.0000
6.500 0.8998 0.01221 0.00582 -0.0313 0.1520 1.0000
6.750 0.9285 0.01273 0.00620 -0.0316 0.1313 1.0000
7.000 0.9571 0.01325 0.00663 -0.0319 0.1177 1.0000
7.250 0.9856 0.01371 0.00704 -0.0321 0.1086 1.0000
7.500 1.0138 0.01421 0.00751 -0.0323 0.1016 1.0000
7.750 1.0421 0.01465 0.00794 -0.0324 0.0962 1.0000
8.000 1.0698 0.01520 0.00847 -0.0326 0.0912 1.0000
8.250 1.0978 0.01560 0.00889 -0.0326 0.0875 1.0000
8.500 1.1249 0.01619 0.00945 -0.0327 0.0836 1.0000
8.750 1.1521 0.01669 0.00998 -0.0328 0.0805 1.0000
9.000 1.1794 0.01712 0.01045 -0.0328 0.0776 1.0000
9.250 1.2057 0.01772 0.01104 -0.0328 0.0748 1.0000
9.500 1.2314 0.01840 0.01173 -0.0327 0.0722 1.0000
9.750 1.2579 0.01884 0.01224 -0.0326 0.0700 1.0000
10.000 1.2838 0.01937 0.01279 -0.0325 0.0678 1.0000
10.250 1.3074 0.02024 0.01364 -0.0323 0.0654 1.0000
10.500 1.3323 0.02083 0.01430 -0.0320 0.0637 1.0000
10.750 1.3572 0.02138 0.01490 -0.0318 0.0619 1.0000
11.000 1.3813 0.02198 0.01554 -0.0315 0.0601 1.0000
11.250 1.4026 0.02290 0.01645 -0.0311 0.0583 1.0000
11.500 1.4243 0.02373 0.01735 -0.0306 0.0568 1.0000
11.750 1.4468 0.02439 0.01809 -0.0301 0.0553 1.0000
12.000 1.4682 0.02510 0.01885 -0.0296 0.0538 1.0000
12.250 1.4877 0.02595 0.01973 -0.0290 0.0524 1.0000
12.500 1.5010 0.02737 0.02115 -0.0279 0.0509 1.0000
12.750 1.5196 0.02815 0.02206 -0.0271 0.0499 1.0000
13.000 1.5352 0.02910 0.02310 -0.0261 0.0487 1.0000
13.250 1.5480 0.03016 0.02424 -0.0250 0.0476 1.0000
13.500 1.5546 0.03150 0.02563 -0.0234 0.0467 1.0000
13.750 1.5562 0.03353 0.02771 -0.0224 0.0458 1.0000
14.000 1.5552 0.03621 0.03046 -0.0220 0.0450 1.0000
14.250 1.5622 0.03838 0.03278 -0.0224 0.0443 1.0000
14.500 1.5673 0.04090 0.03542 -0.0230 0.0435 1.0000
14.750 1.5711 0.04368 0.03831 -0.0238 0.0426 1.0000
15.000 1.5734 0.04671 0.04143 -0.0249 0.0419 1.0000
15.250 1.5740 0.05003 0.04482 -0.0261 0.0412 1.0000
15.500 1.5711 0.05374 0.04859 -0.0273 0.0406 1.0000
15.750 1.5642 0.05778 0.05267 -0.0283 0.0399 1.0000
16.000 1.5592 0.06186 0.05688 -0.0297 0.0394 1.0000
16.250 1.5536 0.06611 0.06129 -0.0314 0.0389 1.0000
16.500 1.5467 0.07056 0.06586 -0.0331 0.0384 1.0000
16.750 1.5386 0.07514 0.07056 -0.0348 0.0378 1.0000
17.000 1.5305 0.07985 0.07537 -0.0367 0.0373 1.0000
17.250 1.5228 0.08463 0.08024 -0.0387 0.0368 1.0000
17.500 1.5151 0.08947 0.08515 -0.0408 0.0363 1.0000
17.750 1.5076 0.09430 0.09005 -0.0428 0.0358 1.0000
18.000 1.5016 0.09870 0.09446 -0.0444 0.0352 1.0000
18.250 1.4921 0.10389 0.09975 -0.0467 0.0348 1.0000
18.500 1.4802 0.10990 0.10591 -0.0497 0.0344 1.0000
18.750 1.4685 0.11592 0.11208 -0.0527 0.0340 1.0000
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