FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 200,000 Max Cl/Cd: 68.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60160-il-200000-n5.txt Download as CSV file: xf-fx60160-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-160 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5417 0.07651 0.07269 -0.0755 1.0000 0.0264
-12.250 -0.5809 0.06887 0.06496 -0.0788 1.0000 0.0263
-12.000 -0.6130 0.06208 0.05800 -0.0825 0.9986 0.0262
-11.750 -0.6444 0.05320 0.04868 -0.0906 0.9914 0.0265
-11.500 -0.6512 0.04841 0.04361 -0.0952 0.9848 0.0269
-11.250 -0.6432 0.04606 0.04116 -0.0976 0.9779 0.0273
-11.000 -0.6305 0.04381 0.03877 -0.1006 0.9722 0.0277
-10.750 -0.6196 0.04232 0.03716 -0.1015 0.9633 0.0283
-10.500 -0.6004 0.03992 0.03455 -0.1042 0.9589 0.0291
-10.250 -0.5919 0.03763 0.03200 -0.1041 0.9494 0.0297
-10.000 -0.5715 0.03492 0.02894 -0.1061 0.9451 0.0308
-9.750 -0.5594 0.03287 0.02655 -0.1055 0.9351 0.0318
-9.500 -0.5358 0.03085 0.02409 -0.1068 0.9302 0.0328
-9.250 -0.5193 0.02912 0.02220 -0.1060 0.9206 0.0334
-8.750 -0.4706 0.02670 0.01958 -0.1069 0.9064 0.0349
-8.500 -0.4423 0.02567 0.01841 -0.1079 0.9005 0.0359
-8.250 -0.4189 0.02479 0.01740 -0.1077 0.8916 0.0371
-8.000 -0.3895 0.02375 0.01619 -0.1087 0.8858 0.0384
-7.750 -0.3639 0.02278 0.01506 -0.1087 0.8776 0.0394
-7.500 -0.3342 0.02186 0.01398 -0.1095 0.8712 0.0403
-7.250 -0.3079 0.02098 0.01300 -0.1096 0.8634 0.0411
-7.000 -0.2804 0.02005 0.01205 -0.1101 0.8568 0.0426
-6.750 -0.2547 0.01944 0.01141 -0.1102 0.8491 0.0441
-6.500 -0.2276 0.01883 0.01073 -0.1105 0.8421 0.0457
-6.250 -0.2026 0.01824 0.01007 -0.1103 0.8347 0.0471
-6.000 -0.1771 0.01770 0.00944 -0.1103 0.8279 0.0487
-5.750 -0.1518 0.01725 0.00889 -0.1102 0.8215 0.0500
-5.500 -0.1293 0.01663 0.00825 -0.1097 0.8144 0.0521
-5.250 -0.1038 0.01613 0.00769 -0.1098 0.8089 0.0547
-5.000 -0.0809 0.01575 0.00728 -0.1093 0.8021 0.0572
-4.750 -0.0556 0.01539 0.00682 -0.1092 0.7964 0.0599
-4.500 -0.0300 0.01505 0.00639 -0.1091 0.7911 0.0625
-4.250 -0.0065 0.01465 0.00599 -0.1088 0.7849 0.0677
-4.000 0.0198 0.01438 0.00563 -0.1088 0.7799 0.0737
-3.750 0.0455 0.01405 0.00529 -0.1088 0.7750 0.0836
-3.500 0.0692 0.01364 0.00503 -0.1085 0.7693 0.1155
-3.250 0.0882 0.01236 0.00453 -0.1082 0.7642 0.3203
-3.000 0.1103 0.01171 0.00444 -0.1077 0.7598 0.4629
-2.750 0.1342 0.01164 0.00461 -0.1069 0.7542 0.5289
-2.500 0.1608 0.01173 0.00474 -0.1065 0.7494 0.5643
-2.250 0.1894 0.01184 0.00478 -0.1066 0.7453 0.5868
-2.000 0.2152 0.01198 0.00491 -0.1061 0.7399 0.6049
-1.750 0.2422 0.01211 0.00499 -0.1059 0.7347 0.6196
-1.500 0.2702 0.01228 0.00509 -0.1057 0.7303 0.6321
-1.250 0.2965 0.01244 0.00525 -0.1053 0.7253 0.6423
-1.000 0.3231 0.01254 0.00528 -0.1051 0.7197 0.6512
-0.750 0.3508 0.01262 0.00533 -0.1050 0.7151 0.6562
-0.500 0.3782 0.01267 0.00532 -0.1050 0.7103 0.6607
-0.250 0.4046 0.01271 0.00532 -0.1048 0.7047 0.6663
0.000 0.4317 0.01279 0.00539 -0.1046 0.6999 0.6709
0.250 0.4592 0.01288 0.00544 -0.1046 0.6953 0.6769
0.500 0.4850 0.01294 0.00549 -0.1043 0.6895 0.6824
0.750 0.5118 0.01299 0.00554 -0.1041 0.6846 0.6859
1.000 0.5393 0.01304 0.00556 -0.1041 0.6799 0.6896
1.250 0.5649 0.01309 0.00562 -0.1038 0.6739 0.6936
1.500 0.5922 0.01313 0.00562 -0.1038 0.6687 0.6973
1.750 0.6190 0.01317 0.00568 -0.1036 0.6636 0.6999
2.000 0.6441 0.01323 0.00578 -0.1032 0.6575 0.7029
2.250 0.6711 0.01328 0.00582 -0.1031 0.6521 0.7063
2.500 0.6973 0.01334 0.00589 -0.1029 0.6464 0.7099
2.750 0.7229 0.01341 0.00598 -0.1026 0.6401 0.7132
3.000 0.7499 0.01346 0.00603 -0.1025 0.6349 0.7158
3.250 0.7740 0.01353 0.00619 -0.1019 0.6280 0.7186
3.500 0.7999 0.01360 0.00628 -0.1016 0.6217 0.7217
3.750 0.8252 0.01368 0.00639 -0.1012 0.6148 0.7252
4.000 0.8499 0.01375 0.00646 -0.1007 0.6061 0.7286
4.250 0.8726 0.01380 0.00658 -0.0998 0.5953 0.7310
4.500 0.8957 0.01387 0.00666 -0.0989 0.5844 0.7338
4.750 0.9177 0.01394 0.00674 -0.0977 0.5710 0.7371
5.000 0.9377 0.01404 0.00684 -0.0963 0.5540 0.7405
5.500 0.9746 0.01435 0.00707 -0.0928 0.5141 0.7465
5.750 0.9924 0.01456 0.00726 -0.0909 0.4958 0.7495
6.000 1.0089 0.01481 0.00749 -0.0889 0.4750 0.7529
6.250 1.0216 0.01514 0.00773 -0.0862 0.4509 0.7564
6.500 1.0314 0.01553 0.00802 -0.0829 0.4243 0.7599
6.750 1.0382 0.01603 0.00843 -0.0793 0.3948 0.7630
7.000 1.0437 0.01667 0.00894 -0.0755 0.3617 0.7666
7.250 1.0438 0.01757 0.00964 -0.0711 0.3166 0.7704
7.500 1.0394 0.01878 0.01054 -0.0663 0.2588 0.7745
7.750 1.0298 0.02036 0.01177 -0.0611 0.1940 0.7782
8.000 1.0118 0.02265 0.01355 -0.0555 0.1059 0.7824
8.250 1.0137 0.02404 0.01481 -0.0525 0.0854 0.7867
8.500 1.0227 0.02511 0.01589 -0.0506 0.0772 0.7908
8.750 1.0322 0.02617 0.01702 -0.0488 0.0715 0.7949
9.000 1.0405 0.02738 0.01829 -0.0471 0.0671 0.7999
9.250 1.0523 0.02840 0.01941 -0.0458 0.0641 0.8052
9.500 1.0627 0.02955 0.02066 -0.0444 0.0613 0.8102
9.750 1.0715 0.03086 0.02204 -0.0431 0.0589 0.8162
10.000 1.0783 0.03236 0.02362 -0.0417 0.0572 0.8230
10.250 1.0858 0.03387 0.02524 -0.0405 0.0556 0.8318
10.500 1.0955 0.03525 0.02677 -0.0395 0.0545 0.8429
10.750 1.1053 0.03670 0.02839 -0.0387 0.0534 0.8601
11.000 1.1182 0.03818 0.03009 -0.0389 0.0523 0.9363
11.250 1.1227 0.03971 0.03168 -0.0373 0.0514 1.0000
11.500 1.1310 0.04138 0.03340 -0.0364 0.0504 1.0000
11.750 1.1394 0.04306 0.03514 -0.0357 0.0494 1.0000
12.000 1.1475 0.04479 0.03691 -0.0350 0.0483 1.0000
12.250 1.1546 0.04663 0.03876 -0.0343 0.0470 1.0000
12.500 1.1623 0.04844 0.04060 -0.0336 0.0458 1.0000
12.750 1.1734 0.04997 0.04224 -0.0332 0.0445 1.0000
13.000 1.1836 0.05161 0.04397 -0.0328 0.0431 1.0000
13.250 1.1931 0.05334 0.04578 -0.0324 0.0416 1.0000
13.500 1.2020 0.05514 0.04766 -0.0321 0.0405 1.0000
13.750 1.2100 0.05706 0.04964 -0.0319 0.0391 1.0000
14.000 1.2167 0.05915 0.05176 -0.0316 0.0379 1.0000
14.250 1.2243 0.06115 0.05381 -0.0313 0.0368 1.0000
14.500 1.2332 0.06308 0.05589 -0.0312 0.0357 1.0000
14.750 1.2413 0.06513 0.05807 -0.0312 0.0343 1.0000
15.000 1.2482 0.06735 0.06039 -0.0313 0.0328 1.0000
15.250 1.2542 0.06972 0.06286 -0.0315 0.0316 1.0000
15.500 1.2587 0.07232 0.06552 -0.0319 0.0304 1.0000
15.750 1.2626 0.07499 0.06825 -0.0321 0.0292 1.0000
16.000 1.2694 0.07738 0.07083 -0.0324 0.0278 1.0000
16.250 1.2745 0.08002 0.07361 -0.0328 0.0263 1.0000
16.500 1.2780 0.08293 0.07662 -0.0335 0.0249 1.0000
16.750 1.2798 0.08615 0.07990 -0.0343 0.0238 1.0000
17.000 1.2834 0.08908 0.08300 -0.0349 0.0222 1.0000
17.250 1.2864 0.09219 0.08625 -0.0357 0.0204 1.0000
17.500 1.2879 0.09557 0.08974 -0.0368 0.0193 1.0000
17.750 1.2888 0.09904 0.09331 -0.0379 0.0182 1.0000
18.000 1.2896 0.10252 0.09694 -0.0389 0.0168 1.0000
18.250 1.2897 0.10621 0.10074 -0.0402 0.0158 1.0000
18.500 1.2888 0.11012 0.10474 -0.0419 0.0151 1.0000
18.750 1.2866 0.11425 0.10898 -0.0435 0.0145 1.0000
19.000 1.2839 0.11850 0.11337 -0.0452 0.0139 1.0000
19.250 1.2802 0.12295 0.11796 -0.0472 0.0135 1.0000
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