OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 200,000 Max Cl/Cd: 88.16 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf095-il-200000.txt Download as CSV file: xf-oaf095-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: OAF095 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4102 0.09626 0.09264 -0.0272 1.0000 0.0759
-8.750 -0.4961 0.06857 0.06515 -0.0482 1.0000 0.0489
-8.500 -0.5438 0.03838 0.03427 -0.0869 1.0000 0.0442
-8.250 -0.5234 0.03222 0.02739 -0.0942 1.0000 0.0460
-8.000 -0.4983 0.02889 0.02337 -0.0976 1.0000 0.0479
-7.750 -0.4736 0.02526 0.01939 -0.1001 1.0000 0.0498
-7.500 -0.4512 0.02404 0.01809 -0.1004 1.0000 0.0519
-7.250 -0.4276 0.02301 0.01687 -0.1007 1.0000 0.0549
-7.000 -0.4020 0.02196 0.01545 -0.1012 1.0000 0.0577
-6.750 -0.3749 0.02013 0.01353 -0.1023 1.0000 0.0609
-6.500 -0.3397 0.01941 0.01269 -0.1044 0.9980 0.0658
-6.250 -0.2991 0.01811 0.01120 -0.1075 0.9955 0.0714
-6.000 -0.2590 0.01743 0.01046 -0.1104 0.9927 0.0783
-5.750 -0.2196 0.01653 0.00952 -0.1132 0.9892 0.0867
-5.500 -0.1788 0.01580 0.00872 -0.1162 0.9861 0.0975
-5.250 -0.1368 0.01519 0.00810 -0.1193 0.9836 0.1116
-5.000 -0.0983 0.01476 0.00767 -0.1218 0.9791 0.1276
-4.750 -0.0581 0.01442 0.00732 -0.1245 0.9751 0.1457
-4.500 -0.0157 0.01412 0.00696 -0.1276 0.9722 0.1654
-4.250 0.0271 0.01373 0.00663 -0.1308 0.9699 0.1847
-4.000 0.0628 0.01350 0.00643 -0.1325 0.9635 0.2028
-3.750 0.1025 0.01326 0.00620 -0.1349 0.9593 0.2227
-3.500 0.1411 0.01308 0.00597 -0.1370 0.9550 0.2424
-3.250 0.1736 0.01291 0.00586 -0.1379 0.9472 0.2598
-3.000 0.2090 0.01271 0.00572 -0.1392 0.9420 0.2774
-2.750 0.2380 0.01263 0.00566 -0.1392 0.9330 0.2940
-2.500 0.2691 0.01252 0.00558 -0.1395 0.9269 0.3115
-2.250 0.2967 0.01247 0.00557 -0.1393 0.9177 0.3285
-2.000 0.3253 0.01239 0.00551 -0.1389 0.9111 0.3468
-1.750 0.3525 0.01237 0.00552 -0.1386 0.9017 0.3653
-1.500 0.3800 0.01231 0.00546 -0.1380 0.8952 0.3846
-1.250 0.4072 0.01228 0.00551 -0.1377 0.8859 0.4030
-1.000 0.4342 0.01221 0.00549 -0.1370 0.8795 0.4218
-0.750 0.4617 0.01219 0.00553 -0.1368 0.8698 0.4410
-0.500 0.4887 0.01212 0.00549 -0.1361 0.8631 0.4603
-0.250 0.5165 0.01210 0.00553 -0.1359 0.8536 0.4800
0.000 0.5437 0.01202 0.00552 -0.1353 0.8467 0.4996
0.250 0.5714 0.01197 0.00556 -0.1351 0.8372 0.5204
0.500 0.5987 0.01190 0.00556 -0.1346 0.8290 0.5432
0.750 0.6258 0.01179 0.00556 -0.1340 0.8196 0.5687
1.000 0.6533 0.01170 0.00561 -0.1336 0.8098 0.5990
1.250 0.6803 0.01155 0.00559 -0.1329 0.8018 0.6384
1.500 0.7067 0.01135 0.00569 -0.1323 0.7911 0.7026
1.750 0.7213 0.01073 0.00553 -0.1285 0.7814 1.0000
2.000 0.7498 0.01075 0.00544 -0.1281 0.7705 1.0000
2.250 0.7778 0.01078 0.00541 -0.1277 0.7566 1.0000
2.500 0.8057 0.01082 0.00540 -0.1273 0.7426 1.0000
2.750 0.8334 0.01088 0.00543 -0.1269 0.7283 1.0000
3.000 0.8610 0.01093 0.00544 -0.1263 0.7128 1.0000
3.250 0.8884 0.01099 0.00544 -0.1258 0.6957 1.0000
3.500 0.9157 0.01107 0.00548 -0.1252 0.6779 1.0000
3.750 0.9430 0.01117 0.00557 -0.1247 0.6576 1.0000
4.000 0.9700 0.01129 0.00566 -0.1242 0.6357 1.0000
4.250 0.9969 0.01145 0.00578 -0.1236 0.6113 1.0000
4.500 1.0232 0.01164 0.00592 -0.1230 0.5827 1.0000
4.750 1.0491 0.01190 0.00609 -0.1223 0.5459 1.0000
5.000 1.0738 0.01230 0.00631 -0.1215 0.4967 1.0000
5.250 1.0962 0.01298 0.00667 -0.1205 0.4214 1.0000
5.500 1.1136 0.01436 0.00735 -0.1190 0.3029 1.0000
5.750 1.1297 0.01606 0.00837 -0.1177 0.1964 1.0000
6.000 1.1471 0.01760 0.00944 -0.1164 0.1330 1.0000
6.250 1.1661 0.01888 0.01050 -0.1152 0.1042 1.0000
6.500 1.1847 0.02014 0.01163 -0.1138 0.0885 1.0000
6.750 1.2054 0.02109 0.01258 -0.1126 0.0782 1.0000
7.000 1.2247 0.02222 0.01373 -0.1112 0.0710 1.0000
7.250 1.2427 0.02345 0.01492 -0.1098 0.0651 1.0000
7.500 1.2622 0.02460 0.01613 -0.1084 0.0604 1.0000
7.750 1.2818 0.02565 0.01720 -0.1071 0.0565 1.0000
8.000 1.2990 0.02765 0.01911 -0.1056 0.0530 1.0000
8.250 1.3202 0.02864 0.02025 -0.1044 0.0506 1.0000
8.500 1.3405 0.02976 0.02148 -0.1032 0.0478 1.0000
8.750 1.3603 0.03105 0.02277 -0.1020 0.0455 1.0000
9.000 1.3838 0.03394 0.02564 -0.1016 0.0433 1.0000
9.250 1.4031 0.03521 0.02716 -0.1001 0.0421 1.0000
9.500 1.4218 0.03676 0.02895 -0.0987 0.0404 1.0000
9.750 1.4396 0.03833 0.03068 -0.0973 0.0388 1.0000
10.000 1.4566 0.04012 0.03261 -0.0960 0.0375 1.0000
10.250 1.4733 0.04222 0.03482 -0.0947 0.0365 1.0000
10.500 1.4896 0.04555 0.03831 -0.0936 0.0356 1.0000
10.750 1.4964 0.04990 0.04301 -0.0915 0.0350 1.0000
11.000 1.4969 0.05215 0.04567 -0.0882 0.0345 1.0000
11.250 1.4931 0.05486 0.04875 -0.0847 0.0340 1.0000
11.500 1.4831 0.05768 0.05190 -0.0807 0.0336 1.0000
11.750 1.4692 0.06091 0.05543 -0.0768 0.0334 1.0000
12.000 1.4526 0.06460 0.05941 -0.0736 0.0332 1.0000
12.250 1.4333 0.06887 0.06397 -0.0713 0.0332 1.0000
12.500 1.4118 0.07366 0.06903 -0.0697 0.0333 1.0000
12.750 1.3884 0.07902 0.07464 -0.0692 0.0335 1.0000
13.000 1.3634 0.08500 0.08086 -0.0697 0.0336 1.0000
13.250 1.3375 0.09161 0.08769 -0.0714 0.0338 1.0000
13.500 1.3110 0.09896 0.09524 -0.0742 0.0341 1.0000
13.750 1.2842 0.10708 0.10353 -0.0781 0.0344 1.0000
14.000 1.2585 0.11587 0.11245 -0.0829 0.0347 1.0000
14.250 1.1445 0.15454 0.15152 -0.1091 0.0432 1.0000
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Polar data table (+)
Polar graphs
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