WORTMANN FX 05-191 AIRFOIL (fx05191-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 05-191 AIRFOIL (fx05191-il) Reynolds number: 500,000 Max Cl/Cd: 89.44 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx05191-il-500000.txt Download as CSV file: xf-fx05191-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 05-191 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4339 0.09378 0.09095 -0.1154 0.9468 0.0248
-15.750 -0.4481 0.08493 0.08201 -0.1221 0.9441 0.0242
-15.500 -0.4788 0.07367 0.07051 -0.1318 0.9401 0.0239
-15.250 -0.5098 0.06382 0.06035 -0.1401 0.9353 0.0235
-15.000 -0.5331 0.05616 0.05236 -0.1463 0.9303 0.0234
-14.750 -0.5481 0.05124 0.04718 -0.1491 0.9242 0.0234
-14.500 -0.5608 0.04706 0.04272 -0.1507 0.9185 0.0234
-14.250 -0.5725 0.04308 0.03843 -0.1517 0.9138 0.0235
-14.000 -0.5783 0.04047 0.03561 -0.1512 0.9093 0.0236
-13.750 -0.5806 0.03820 0.03314 -0.1504 0.9052 0.0238
-13.500 -0.5788 0.03598 0.03069 -0.1498 0.9017 0.0239
-13.250 -0.5730 0.03419 0.02868 -0.1492 0.8986 0.0241
-13.000 -0.5689 0.03288 0.02720 -0.1480 0.8954 0.0245
-12.750 -0.5663 0.03182 0.02597 -0.1464 0.8920 0.0248
-12.500 -0.5571 0.03053 0.02451 -0.1453 0.8894 0.0249
-12.250 -0.5263 0.02851 0.02242 -0.1462 0.8883 0.0257
-12.000 -0.5065 0.02757 0.02142 -0.1460 0.8864 0.0260
-11.750 -0.4874 0.02675 0.02055 -0.1457 0.8845 0.0264
-11.500 -0.4672 0.02596 0.01968 -0.1455 0.8826 0.0268
-11.250 -0.4477 0.02528 0.01894 -0.1451 0.8808 0.0273
-11.000 -0.4288 0.02458 0.01820 -0.1445 0.8789 0.0279
-10.750 -0.4101 0.02393 0.01750 -0.1437 0.8767 0.0285
-10.500 -0.3915 0.02335 0.01685 -0.1430 0.8742 0.0289
-10.250 -0.3746 0.02286 0.01627 -0.1421 0.8714 0.0296
-10.000 -0.3538 0.02206 0.01544 -0.1415 0.8688 0.0303
-9.750 -0.3364 0.02142 0.01479 -0.1407 0.8660 0.0309
-9.500 -0.3214 0.02086 0.01423 -0.1394 0.8635 0.0317
-9.250 -0.3072 0.02033 0.01369 -0.1381 0.8612 0.0324
-9.000 -0.2927 0.01981 0.01316 -0.1367 0.8587 0.0334
-8.750 -0.2782 0.01929 0.01260 -0.1353 0.8562 0.0341
-8.500 -0.2629 0.01880 0.01207 -0.1340 0.8538 0.0349
-8.250 -0.2513 0.01814 0.01136 -0.1323 0.8512 0.0361
-8.000 -0.2390 0.01759 0.01080 -0.1307 0.8488 0.0374
-7.750 -0.2271 0.01713 0.01035 -0.1287 0.8463 0.0388
-7.500 -0.2142 0.01672 0.00994 -0.1269 0.8434 0.0404
-7.250 -0.2000 0.01634 0.00952 -0.1251 0.8406 0.0419
-7.000 -0.1918 0.01570 0.00889 -0.1226 0.8375 0.0448
-6.750 -0.1769 0.01528 0.00844 -0.1210 0.8349 0.0479
-6.500 -0.1644 0.01486 0.00800 -0.1190 0.8322 0.0529
-6.250 -0.1583 0.01452 0.00770 -0.1157 0.8291 0.0610
-6.000 -0.1555 0.01414 0.00740 -0.1118 0.8254 0.0742
-5.750 -0.1480 0.01356 0.00698 -0.1091 0.8218 0.1088
-5.500 -0.1421 0.01262 0.00643 -0.1065 0.8186 0.1958
-5.250 -0.1363 0.01128 0.00574 -0.1044 0.8157 0.3498
-5.000 -0.1198 0.01053 0.00544 -0.1035 0.8126 0.4600
-4.750 -0.0953 0.01027 0.00530 -0.1034 0.8093 0.5046
-4.500 -0.0679 0.01007 0.00516 -0.1037 0.8062 0.5346
-4.250 -0.0388 0.00991 0.00502 -0.1043 0.8035 0.5564
-4.000 -0.0084 0.00979 0.00490 -0.1050 0.8012 0.5754
-3.750 0.0228 0.00971 0.00483 -0.1059 0.7990 0.5964
-3.500 0.0500 0.00968 0.00483 -0.1061 0.7957 0.6198
-3.250 0.0772 0.00966 0.00486 -0.1061 0.7918 0.6386
-3.000 0.1060 0.00963 0.00485 -0.1063 0.7886 0.6516
-2.750 0.1360 0.00958 0.00479 -0.1068 0.7858 0.6598
-2.500 0.1678 0.00952 0.00466 -0.1078 0.7832 0.6668
-2.250 0.1961 0.00949 0.00462 -0.1081 0.7797 0.6729
-2.000 0.2226 0.00946 0.00462 -0.1079 0.7752 0.6785
-1.750 0.2528 0.00940 0.00451 -0.1086 0.7715 0.6854
-1.500 0.2828 0.00934 0.00444 -0.1091 0.7684 0.6903
-1.250 0.3133 0.00933 0.00440 -0.1098 0.7652 0.6956
-1.000 0.3400 0.00930 0.00437 -0.1098 0.7597 0.7023
-0.750 0.3678 0.00927 0.00436 -0.1098 0.7551 0.7064
-0.500 0.3975 0.00926 0.00432 -0.1103 0.7514 0.7108
-0.250 0.4257 0.00926 0.00431 -0.1105 0.7463 0.7166
0.000 0.4529 0.00925 0.00430 -0.1106 0.7405 0.7211
0.250 0.4813 0.00925 0.00429 -0.1107 0.7357 0.7245
0.500 0.5077 0.00930 0.00435 -0.1105 0.7295 0.7287
0.750 0.5364 0.00930 0.00432 -0.1109 0.7233 0.7341
1.000 0.5649 0.00932 0.00431 -0.1112 0.7180 0.7375
1.250 0.5889 0.00940 0.00444 -0.1104 0.7102 0.7404
1.500 0.6167 0.00946 0.00446 -0.1105 0.7041 0.7437
1.750 0.6431 0.00954 0.00454 -0.1105 0.6967 0.7480
2.000 0.6722 0.00959 0.00453 -0.1110 0.6901 0.7525
2.250 0.6966 0.00970 0.00467 -0.1104 0.6832 0.7548
2.500 0.7216 0.00983 0.00479 -0.1099 0.6761 0.7574
2.750 0.7480 0.00996 0.00491 -0.1098 0.6699 0.7604
3.000 0.7739 0.01008 0.00503 -0.1096 0.6630 0.7642
3.250 0.8047 0.01021 0.00508 -0.1106 0.6569 0.7686
3.500 0.8267 0.01032 0.00525 -0.1096 0.6497 0.7707
3.750 0.8511 0.01049 0.00540 -0.1090 0.6425 0.7729
4.000 0.8743 0.01065 0.00558 -0.1082 0.6352 0.7755
4.250 0.8986 0.01079 0.00573 -0.1077 0.6278 0.7785
4.500 0.9243 0.01095 0.00586 -0.1076 0.6204 0.7822
4.750 0.9493 0.01106 0.00599 -0.1075 0.6130 0.7857
5.000 0.9730 0.01123 0.00614 -0.1068 0.6064 0.7877
5.250 0.9907 0.01133 0.00632 -0.1049 0.5979 0.7900
5.500 1.0104 0.01150 0.00648 -0.1035 0.5885 0.7925
5.750 1.0273 0.01162 0.00663 -0.1016 0.5786 0.7958
6.000 1.0451 0.01176 0.00677 -0.0999 0.5690 0.7995
6.250 1.0634 0.01191 0.00691 -0.0984 0.5596 0.8024
6.500 1.0786 0.01206 0.00712 -0.0962 0.5512 0.8046
6.750 1.0935 0.01232 0.00737 -0.0939 0.5419 0.8071
7.000 1.1079 0.01257 0.00768 -0.0917 0.5307 0.8102
7.250 1.1220 0.01290 0.00800 -0.0896 0.5179 0.8135
7.500 1.1358 0.01331 0.00839 -0.0876 0.5024 0.8170
7.750 1.1466 0.01372 0.00879 -0.0850 0.4870 0.8195
8.000 1.1563 0.01420 0.00927 -0.0823 0.4710 0.8219
8.250 1.1646 0.01480 0.00985 -0.0795 0.4509 0.8246
8.500 1.1693 0.01563 0.01059 -0.0763 0.4255 0.8277
8.750 1.1714 0.01671 0.01154 -0.0731 0.3913 0.8308
9.000 1.1661 0.01829 0.01287 -0.0692 0.3445 0.8335
9.250 1.1570 0.01998 0.01432 -0.0647 0.2971 0.8358
9.500 1.1470 0.02192 0.01599 -0.0604 0.2457 0.8381
9.750 1.1397 0.02388 0.01769 -0.0567 0.1993 0.8403
10.250 1.1345 0.02766 0.02107 -0.0512 0.1260 0.8449
10.500 1.1382 0.02933 0.02262 -0.0494 0.1044 0.8468
10.750 1.1462 0.03080 0.02404 -0.0482 0.0934 0.8485
11.000 1.1548 0.03214 0.02538 -0.0469 0.0861 0.8503
11.250 1.1628 0.03353 0.02678 -0.0456 0.0804 0.8519
11.500 1.1709 0.03499 0.02828 -0.0444 0.0754 0.8535
11.750 1.1818 0.03628 0.02962 -0.0435 0.0709 0.8552
12.000 1.1873 0.03808 0.03142 -0.0423 0.0661 0.8570
12.250 1.2003 0.03934 0.03274 -0.0418 0.0622 0.8587
12.500 1.2097 0.04095 0.03437 -0.0412 0.0578 0.8602
12.750 1.2184 0.04269 0.03614 -0.0406 0.0538 0.8618
13.000 1.2298 0.04424 0.03772 -0.0402 0.0502 0.8633
13.250 1.2349 0.04640 0.03987 -0.0396 0.0466 0.8647
13.500 1.2468 0.04786 0.04141 -0.0393 0.0439 0.8661
13.750 1.2550 0.04970 0.04328 -0.0388 0.0415 0.8673
14.000 1.2584 0.05208 0.04568 -0.0382 0.0392 0.8686
14.250 1.2683 0.05385 0.04754 -0.0380 0.0376 0.8699
14.500 1.2770 0.05576 0.04952 -0.0378 0.0358 0.8714
14.750 1.2824 0.05809 0.05187 -0.0376 0.0342 0.8730
15.000 1.2854 0.06073 0.05457 -0.0374 0.0328 0.8744
15.250 1.2944 0.06281 0.05673 -0.0374 0.0316 0.8758
15.500 1.3023 0.06503 0.05902 -0.0376 0.0304 0.8771
15.750 1.3085 0.06749 0.06153 -0.0378 0.0293 0.8782
16.000 1.3099 0.07056 0.06462 -0.0380 0.0282 0.8792
16.250 1.3143 0.07329 0.06744 -0.0383 0.0273 0.8802
16.500 1.3213 0.07569 0.06995 -0.0386 0.0264 0.8815
16.750 1.3275 0.07819 0.07253 -0.0389 0.0254 0.8827
17.000 1.3321 0.08091 0.07532 -0.0393 0.0246 0.8841
17.250 1.3343 0.08396 0.07841 -0.0398 0.0238 0.8855
17.500 1.3333 0.08742 0.08192 -0.0403 0.0230 0.8867
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 05-191 AIRFOIL (fx05191-il)