FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-157 AIRFOIL (fx60157-il) Reynolds number: 500,000 Max Cl/Cd: 81.15 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60157-il-500000.txt Download as CSV file: xf-fx60157-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-157 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7670 0.04987 0.04611 -0.0896 0.9930 0.0101
-13.000 -0.7512 0.04893 0.04521 -0.0909 0.9906 0.0104
-12.750 -0.7687 0.04326 0.03913 -0.0929 0.9871 0.0103
-12.500 -0.7668 0.03978 0.03539 -0.0946 0.9848 0.0103
-12.250 -0.7520 0.03792 0.03340 -0.0966 0.9832 0.0105
-12.000 -0.7460 0.03581 0.03111 -0.0966 0.9798 0.0107
-11.750 -0.7359 0.03424 0.02940 -0.0966 0.9757 0.0109
-11.500 -0.7219 0.03227 0.02724 -0.0973 0.9732 0.0111
-11.250 -0.7024 0.03073 0.02553 -0.0985 0.9714 0.0114
-11.000 -0.6806 0.02902 0.02361 -0.0998 0.9701 0.0117
-10.750 -0.6745 0.02803 0.02248 -0.0974 0.9643 0.0120
-10.500 -0.6570 0.02691 0.02118 -0.0972 0.9611 0.0122
-10.250 -0.6357 0.02555 0.01979 -0.0976 0.9592 0.0127
-10.000 -0.6110 0.02457 0.01876 -0.0985 0.9576 0.0130
-9.750 -0.5839 0.02367 0.01780 -0.0998 0.9564 0.0135
-9.500 -0.5809 0.02316 0.01722 -0.0962 0.9495 0.0141
-9.250 -0.5625 0.02238 0.01635 -0.0956 0.9461 0.0146
-9.000 -0.5372 0.02164 0.01551 -0.0961 0.9441 0.0153
-8.750 -0.5120 0.02043 0.01433 -0.0971 0.9425 0.0166
-8.500 -0.4814 0.01954 0.01336 -0.0988 0.9415 0.0182
-8.250 -0.4806 0.01903 0.01279 -0.0946 0.9335 0.0190
-8.000 -0.4602 0.01805 0.01181 -0.0945 0.9305 0.0215
-7.750 -0.4317 0.01731 0.01106 -0.0957 0.9289 0.0250
-7.500 -0.3988 0.01684 0.01057 -0.0973 0.9280 0.0277
-7.250 -0.3640 0.01649 0.01023 -0.0993 0.9272 0.0303
-7.000 -0.3285 0.01615 0.00983 -0.1013 0.9266 0.0324
-6.750 -0.2943 0.01556 0.00925 -0.1035 0.9259 0.0346
-6.500 -0.2963 0.01547 0.00913 -0.0979 0.9172 0.0354
-6.250 -0.2652 0.01508 0.00871 -0.0991 0.9154 0.0374
-6.000 -0.2309 0.01455 0.00815 -0.1010 0.9141 0.0396
-5.750 -0.1951 0.01398 0.00757 -0.1032 0.9131 0.0433
-5.500 -0.1596 0.01344 0.00707 -0.1053 0.9119 0.0503
-5.250 -0.1242 0.01293 0.00662 -0.1074 0.9109 0.0663
-5.000 -0.0883 0.01224 0.00610 -0.1099 0.9098 0.1069
-4.750 -0.0786 0.01178 0.00590 -0.1070 0.9024 0.1638
-4.500 -0.0455 0.01064 0.00532 -0.1096 0.8999 0.3020
-4.250 -0.0078 0.00981 0.00484 -0.1127 0.8981 0.4002
-4.000 0.0321 0.00906 0.00445 -0.1160 0.8965 0.5026
-3.750 0.0720 0.00865 0.00428 -0.1188 0.8949 0.5748
-3.500 0.1072 0.00855 0.00424 -0.1203 0.8924 0.6094
-3.250 0.1290 0.00859 0.00428 -0.1190 0.8866 0.6269
-3.000 0.1603 0.00857 0.00425 -0.1197 0.8833 0.6406
-2.750 0.1951 0.00854 0.00419 -0.1210 0.8805 0.6523
-2.500 0.2315 0.00852 0.00412 -0.1227 0.8781 0.6636
-2.250 0.2556 0.00865 0.00425 -0.1218 0.8725 0.6744
-2.000 0.2839 0.00874 0.00434 -0.1216 0.8675 0.6831
-1.750 0.3186 0.00876 0.00431 -0.1228 0.8635 0.6917
-1.500 0.3459 0.00878 0.00433 -0.1225 0.8578 0.6963
-1.250 0.3720 0.00885 0.00441 -0.1219 0.8517 0.7007
-1.000 0.4042 0.00887 0.00439 -0.1226 0.8474 0.7058
-0.750 0.4325 0.00888 0.00437 -0.1227 0.8411 0.7108
-0.500 0.4578 0.00894 0.00446 -0.1219 0.8343 0.7143
-0.250 0.4879 0.00900 0.00450 -0.1221 0.8285 0.7180
0.000 0.5118 0.00903 0.00453 -0.1212 0.8195 0.7221
0.250 0.5423 0.00898 0.00441 -0.1218 0.8103 0.7256
0.500 0.5700 0.00891 0.00429 -0.1216 0.7985 0.7279
0.750 0.5939 0.00889 0.00427 -0.1207 0.7853 0.7296
1.000 0.6186 0.00892 0.00428 -0.1199 0.7712 0.7317
1.250 0.6440 0.00897 0.00431 -0.1194 0.7583 0.7341
1.500 0.6698 0.00903 0.00433 -0.1189 0.7446 0.7370
1.750 0.6957 0.00909 0.00433 -0.1186 0.7284 0.7402
2.000 0.7213 0.00918 0.00433 -0.1182 0.7079 0.7431
2.250 0.7430 0.00927 0.00434 -0.1169 0.6850 0.7448
2.500 0.7634 0.00943 0.00440 -0.1153 0.6586 0.7465
2.750 0.7823 0.00964 0.00451 -0.1135 0.6295 0.7485
3.000 0.7981 0.00994 0.00465 -0.1111 0.5942 0.7508
3.250 0.8135 0.01026 0.00480 -0.1087 0.5583 0.7533
3.500 0.8270 0.01061 0.00496 -0.1059 0.5224 0.7560
3.750 0.8421 0.01100 0.00516 -0.1037 0.4865 0.7584
4.000 0.8585 0.01132 0.00534 -0.1017 0.4550 0.7602
4.250 0.8751 0.01167 0.00556 -0.0997 0.4238 0.7618
4.500 0.8930 0.01203 0.00583 -0.0980 0.3983 0.7635
5.000 0.9304 0.01278 0.00638 -0.0950 0.3476 0.7674
5.250 0.9504 0.01316 0.00666 -0.0939 0.3248 0.7694
5.500 0.9704 0.01356 0.00696 -0.0928 0.3016 0.7713
5.750 0.9912 0.01394 0.00726 -0.0919 0.2831 0.7733
6.000 1.0119 0.01436 0.00758 -0.0910 0.2614 0.7751
6.500 1.0497 0.01519 0.00827 -0.0885 0.2251 0.7785
6.750 1.0684 0.01562 0.00865 -0.0872 0.2067 0.7804
7.000 1.0871 0.01609 0.00905 -0.0859 0.1884 0.7824
7.250 1.1060 0.01656 0.00947 -0.0848 0.1759 0.7847
7.500 1.1258 0.01700 0.00988 -0.0838 0.1641 0.7870
7.750 1.1456 0.01747 0.01031 -0.0828 0.1488 0.7891
8.000 1.1644 0.01803 0.01080 -0.0818 0.1361 0.7911
8.250 1.1835 0.01849 0.01126 -0.0808 0.1265 0.7929
8.500 1.2010 0.01902 0.01178 -0.0795 0.1179 0.7947
9.000 1.2353 0.02018 0.01291 -0.0770 0.0959 0.7982
9.250 1.2518 0.02082 0.01355 -0.0756 0.0869 0.8004
9.500 1.2683 0.02150 0.01423 -0.0744 0.0786 0.8025
9.750 1.2824 0.02237 0.01502 -0.0729 0.0625 0.8045
10.000 1.2960 0.02331 0.01591 -0.0714 0.0528 0.8064
10.250 1.3107 0.02417 0.01678 -0.0701 0.0415 0.8081
10.500 1.3197 0.02537 0.01791 -0.0681 0.0328 0.8098
10.750 1.3304 0.02647 0.01903 -0.0664 0.0292 0.8116
11.000 1.3439 0.02739 0.02005 -0.0650 0.0273 0.8135
11.250 1.3555 0.02848 0.02121 -0.0635 0.0257 0.8155
11.500 1.3650 0.02976 0.02256 -0.0618 0.0244 0.8175
11.750 1.3775 0.03084 0.02372 -0.0606 0.0237 0.8198
12.000 1.3905 0.03192 0.02487 -0.0595 0.0228 0.8221
12.250 1.4027 0.03307 0.02610 -0.0584 0.0219 0.8242
12.500 1.4135 0.03429 0.02740 -0.0572 0.0210 0.8263
12.750 1.4224 0.03570 0.02887 -0.0560 0.0203 0.8283
13.000 1.4295 0.03731 0.03057 -0.0547 0.0198 0.8305
13.250 1.4389 0.03879 0.03214 -0.0537 0.0194 0.8328
13.500 1.4471 0.04043 0.03387 -0.0527 0.0190 0.8353
13.750 1.4547 0.04220 0.03574 -0.0519 0.0187 0.8376
14.000 1.4617 0.04409 0.03771 -0.0511 0.0183 0.8399
14.250 1.4674 0.04607 0.03981 -0.0504 0.0180 0.8422
14.500 1.4721 0.04823 0.04207 -0.0497 0.0177 0.8447
14.750 1.4757 0.05060 0.04453 -0.0492 0.0174 0.8473
15.000 1.4782 0.05320 0.04723 -0.0488 0.0171 0.8501
15.250 1.4787 0.05616 0.05029 -0.0486 0.0169 0.8530
15.500 1.4774 0.05949 0.05373 -0.0487 0.0166 0.8557
15.750 1.4736 0.06314 0.05752 -0.0489 0.0164 0.8584
16.000 1.4721 0.06665 0.06117 -0.0493 0.0163 0.8613
16.250 1.4705 0.07033 0.06498 -0.0500 0.0161 0.8643
16.500 1.4682 0.07428 0.06906 -0.0509 0.0160 0.8673
16.750 1.4657 0.07842 0.07333 -0.0522 0.0157 0.8702
17.000 1.4619 0.08277 0.07782 -0.0535 0.0155 0.8731
17.250 1.4572 0.08735 0.08253 -0.0551 0.0152 0.8761
17.500 1.4514 0.09225 0.08758 -0.0570 0.0150 0.8792
17.750 1.4445 0.09746 0.09292 -0.0592 0.0148 0.8826
18.000 1.4369 0.10294 0.09852 -0.0616 0.0146 0.8860
18.250 1.4284 0.10853 0.10425 -0.0642 0.0144 0.8893
18.500 1.4186 0.11441 0.11026 -0.0670 0.0142 0.8931
18.750 1.4091 0.12032 0.11629 -0.0700 0.0140 0.8973
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