FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-157 AIRFOIL (fx60157-il) Reynolds number: 50,000 Max Cl/Cd: 28.59 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60157-il-50000-n5.txt Download as CSV file: xf-fx60157-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4903 0.10576 0.09865 -0.0585 1.0000 0.0457
-11.500 -0.5072 0.10006 0.09299 -0.0602 1.0000 0.0455
-11.250 -0.5251 0.09492 0.08788 -0.0614 1.0000 0.0451
-11.000 -0.5491 0.08969 0.08265 -0.0624 1.0000 0.0448
-10.750 -0.5736 0.08522 0.07816 -0.0626 1.0000 0.0445
-10.500 -0.5998 0.08124 0.07415 -0.0619 1.0000 0.0442
-10.250 -0.6277 0.07775 0.07060 -0.0603 1.0000 0.0439
-10.000 -0.6554 0.07491 0.06770 -0.0578 1.0000 0.0437
-9.750 -0.6824 0.07253 0.06528 -0.0543 1.0000 0.0433
-9.500 -0.7097 0.07014 0.06278 -0.0506 1.0000 0.0432
-9.250 -0.7295 0.06737 0.05983 -0.0475 1.0000 0.0432
-9.000 -0.7458 0.06434 0.05657 -0.0446 1.0000 0.0436
-8.500 -0.7637 0.05796 0.04949 -0.0394 1.0000 0.0446
-8.250 -0.7649 0.05478 0.04586 -0.0372 1.0000 0.0453
-8.000 -0.7593 0.05220 0.04304 -0.0355 1.0000 0.0466
-7.750 -0.7494 0.05045 0.04124 -0.0341 1.0000 0.0490
-7.500 -0.7395 0.04820 0.03862 -0.0326 1.0000 0.0517
-7.250 -0.7277 0.04601 0.03606 -0.0312 1.0000 0.0550
-7.000 -0.7130 0.04443 0.03441 -0.0300 1.0000 0.0583
-6.750 -0.6911 0.04263 0.03208 -0.0297 0.9982 0.0630
-6.500 -0.6641 0.04100 0.03043 -0.0300 0.9952 0.0666
-6.250 -0.6361 0.03971 0.02898 -0.0299 0.9923 0.0706
-6.000 -0.6090 0.03865 0.02777 -0.0295 0.9889 0.0759
-5.750 -0.5812 0.03788 0.02696 -0.0293 0.9854 0.0810
-5.500 -0.5523 0.03725 0.02618 -0.0290 0.9821 0.0865
-5.250 -0.5306 0.03641 0.02534 -0.0285 0.9777 0.0942
-5.000 -0.5072 0.03556 0.02447 -0.0285 0.9732 0.1047
-4.750 -0.4818 0.03465 0.02360 -0.0292 0.9694 0.1197
-4.500 -0.4633 0.03343 0.02260 -0.0290 0.9643 0.1484
-4.250 -0.4438 0.03130 0.02140 -0.0303 0.9598 0.2486
-4.000 -0.4323 0.03083 0.02272 -0.0261 0.9556 0.4986
-3.750 -0.4178 0.03207 0.02408 -0.0211 0.9490 0.5846
-3.250 -0.3720 0.03469 0.02627 -0.0167 0.9368 0.6877
-3.000 -0.3566 0.03622 0.02766 -0.0117 0.9299 0.7227
-2.750 -0.3330 0.03759 0.02888 -0.0083 0.9250 0.7503
-2.500 -0.3185 0.03783 0.02895 -0.0052 0.9176 0.7668
-2.250 -0.2923 0.03792 0.02882 -0.0051 0.9120 0.7796
-2.000 -0.2696 0.03782 0.02852 -0.0048 0.9055 0.7912
-1.750 -0.2449 0.03777 0.02830 -0.0043 0.8984 0.7987
-1.500 -0.2126 0.03766 0.02796 -0.0061 0.8929 0.8079
-1.250 -0.1949 0.03749 0.02767 -0.0044 0.8841 0.8145
-1.000 -0.1639 0.03740 0.02740 -0.0058 0.8783 0.8236
-0.750 -0.1457 0.03728 0.02718 -0.0043 0.8699 0.8303
-0.500 -0.1170 0.03719 0.02694 -0.0052 0.8636 0.8384
-0.250 -0.0962 0.03707 0.02674 -0.0044 0.8553 0.8449
0.000 -0.0678 0.03697 0.02653 -0.0050 0.8482 0.8525
0.250 -0.0463 0.03682 0.02631 -0.0044 0.8391 0.8594
0.500 -0.0156 0.03668 0.02608 -0.0053 0.8318 0.8653
0.750 0.0036 0.03654 0.02586 -0.0047 0.8220 0.8712
1.000 0.0367 0.03640 0.02566 -0.0060 0.8154 0.8751
1.250 0.0556 0.03633 0.02556 -0.0052 0.8053 0.8802
1.500 0.0893 0.03618 0.02533 -0.0068 0.7988 0.8849
1.750 0.1081 0.03609 0.02523 -0.0059 0.7874 0.8899
2.000 0.1433 0.03584 0.02496 -0.0073 0.7803 0.8943
2.250 0.1643 0.03574 0.02484 -0.0068 0.7688 0.8993
2.500 0.1872 0.03566 0.02476 -0.0066 0.7579 0.9035
2.750 0.2228 0.03538 0.02449 -0.0081 0.7507 0.9067
3.000 0.2432 0.03536 0.02449 -0.0076 0.7383 0.9111
3.250 0.2704 0.03518 0.02432 -0.0079 0.7278 0.9153
3.500 0.3047 0.03478 0.02396 -0.0089 0.7188 0.9187
3.750 0.3275 0.03473 0.02396 -0.0086 0.7058 0.9225
4.000 0.3554 0.03455 0.02382 -0.0090 0.6950 0.9265
4.250 0.3901 0.03404 0.02337 -0.0099 0.6862 0.9305
4.500 0.4151 0.03388 0.02330 -0.0098 0.6728 0.9347
4.750 0.4437 0.03357 0.02306 -0.0100 0.6603 0.9389
5.000 0.4846 0.03270 0.02226 -0.0114 0.6523 0.9427
5.250 0.5104 0.03257 0.02224 -0.0113 0.6379 0.9474
5.500 0.5398 0.03233 0.02210 -0.0118 0.6239 0.9519
5.750 0.5718 0.03194 0.02180 -0.0124 0.6100 0.9567
6.000 0.6068 0.03144 0.02141 -0.0133 0.5953 0.9612
6.250 0.6423 0.03098 0.02104 -0.0143 0.5792 0.9660
6.500 0.6769 0.03063 0.02078 -0.0153 0.5623 0.9715
6.750 0.7138 0.03032 0.02056 -0.0167 0.5448 0.9768
7.000 0.7486 0.03008 0.02039 -0.0178 0.5258 0.9837
7.250 0.7799 0.02983 0.02018 -0.0184 0.5059 0.9972
7.500 0.8070 0.02986 0.02019 -0.0184 0.4849 1.0000
7.750 0.8289 0.03025 0.02061 -0.0181 0.4630 1.0000
8.000 0.8529 0.03069 0.02108 -0.0182 0.4422 1.0000
8.250 0.8788 0.03114 0.02153 -0.0184 0.4227 1.0000
8.500 0.9049 0.03165 0.02203 -0.0188 0.4037 1.0000
8.750 0.9249 0.03248 0.02292 -0.0187 0.3842 1.0000
9.000 0.9441 0.03334 0.02383 -0.0185 0.3647 1.0000
9.250 0.9639 0.03422 0.02473 -0.0184 0.3460 1.0000
9.500 0.9841 0.03518 0.02575 -0.0184 0.3288 1.0000
9.750 1.0048 0.03621 0.02685 -0.0185 0.3129 1.0000
10.000 1.0266 0.03726 0.02797 -0.0188 0.2987 1.0000
10.250 1.0488 0.03833 0.02910 -0.0190 0.2849 1.0000
10.500 1.0685 0.03947 0.03029 -0.0191 0.2708 1.0000
10.750 1.0830 0.04081 0.03174 -0.0187 0.2567 1.0000
11.000 1.0941 0.04233 0.03338 -0.0182 0.2431 1.0000
11.250 1.1058 0.04390 0.03507 -0.0178 0.2305 1.0000
11.500 1.1199 0.04544 0.03672 -0.0175 0.2191 1.0000
11.750 1.1342 0.04692 0.03822 -0.0173 0.2080 1.0000
12.000 1.1387 0.04906 0.04061 -0.0167 0.1969 1.0000
12.250 1.1436 0.05112 0.04280 -0.0161 0.1862 1.0000
12.500 1.1484 0.05309 0.04477 -0.0157 0.1758 1.0000
12.750 1.1471 0.05575 0.04761 -0.0153 0.1653 1.0000
13.000 1.1455 0.05860 0.05065 -0.0151 0.1556 1.0000
13.250 1.1463 0.06119 0.05326 -0.0151 0.1468 1.0000
13.500 1.1436 0.06456 0.05688 -0.0153 0.1383 1.0000
13.750 1.1439 0.06754 0.05990 -0.0157 0.1308 1.0000
14.000 1.1387 0.07143 0.06400 -0.0164 0.1230 1.0000
14.250 1.1350 0.07519 0.06782 -0.0173 0.1159 1.0000
14.500 1.1269 0.07982 0.07268 -0.0188 0.1090 1.0000
14.750 1.1218 0.08409 0.07702 -0.0203 0.1029 1.0000
15.000 1.1131 0.08923 0.08236 -0.0224 0.0973 1.0000
15.250 1.1145 0.09257 0.08560 -0.0238 0.0922 1.0000
15.500 1.0992 0.09942 0.09281 -0.0269 0.0882 1.0000
15.750 1.0886 0.10549 0.09906 -0.0299 0.0843 1.0000
16.000 1.0952 0.10811 0.10159 -0.0310 0.0800 1.0000
16.250 1.0720 0.11725 0.11106 -0.0360 0.0780 1.0000
16.500 1.0400 0.12884 0.12294 -0.0428 0.0766 1.0000
16.750 0.9860 0.14711 0.14138 -0.0538 0.0758 1.0000
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