FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-177 AIRFOIL (fx60177-il) Reynolds number: 500,000 Max Cl/Cd: 81.51 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60177-il-500000.txt Download as CSV file: xf-fx60177-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-177 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6117 0.11354 0.11091 -0.0571 1.0001 0.0097
-15.500 -0.6441 0.10335 0.10061 -0.0617 1.0001 0.0095
-15.250 -0.6737 0.09468 0.09181 -0.0655 1.0001 0.0094
-15.000 -0.6982 0.08609 0.08306 -0.0706 0.9997 0.0093
-14.750 -0.7181 0.07756 0.07432 -0.0766 0.9985 0.0092
-14.500 -0.7354 0.07015 0.06669 -0.0817 0.9971 0.0091
-14.250 -0.7500 0.06363 0.05993 -0.0860 0.9957 0.0090
-14.000 -0.7617 0.05794 0.05398 -0.0894 0.9944 0.0089
-13.750 -0.7716 0.05320 0.04898 -0.0912 0.9923 0.0087
-13.500 -0.7778 0.04900 0.04451 -0.0925 0.9898 0.0086
-13.250 -0.7781 0.04537 0.04061 -0.0936 0.9877 0.0085
-13.000 -0.7722 0.04239 0.03739 -0.0947 0.9861 0.0084
-12.750 -0.7608 0.03997 0.03477 -0.0957 0.9849 0.0083
-12.500 -0.7451 0.03791 0.03254 -0.0969 0.9840 0.0083
-12.250 -0.7367 0.03628 0.03079 -0.0960 0.9800 0.0083
-12.000 -0.7222 0.03469 0.02909 -0.0961 0.9773 0.0083
-11.750 -0.7046 0.03320 0.02749 -0.0967 0.9754 0.0083
-11.500 -0.6846 0.03180 0.02600 -0.0976 0.9739 0.0084
-11.250 -0.6628 0.03046 0.02458 -0.0988 0.9727 0.0085
-11.000 -0.6395 0.02918 0.02321 -0.1002 0.9718 0.0086
-10.750 -0.6354 0.02825 0.02223 -0.0975 0.9652 0.0086
-10.500 -0.6159 0.02712 0.02103 -0.0980 0.9628 0.0088
-10.250 -0.5939 0.02599 0.01984 -0.0989 0.9611 0.0089
-10.000 -0.5695 0.02488 0.01867 -0.1003 0.9597 0.0091
-9.750 -0.5431 0.02381 0.01754 -0.1020 0.9587 0.0093
-9.500 -0.5446 0.02325 0.01693 -0.0977 0.9503 0.0095
-9.250 -0.5214 0.02235 0.01597 -0.0984 0.9480 0.0097
-9.000 -0.4965 0.02129 0.01486 -0.0996 0.9464 0.0102
-8.750 -0.4681 0.02037 0.01392 -0.1012 0.9452 0.0109
-8.500 -0.4755 0.02007 0.01359 -0.0954 0.9358 0.0112
-8.250 -0.4526 0.01937 0.01284 -0.0955 0.9334 0.0124
-8.000 -0.4257 0.01847 0.01191 -0.0967 0.9319 0.0156
-7.750 -0.3955 0.01758 0.01106 -0.0985 0.9308 0.0223
-7.500 -0.4009 0.01732 0.01080 -0.0930 0.9215 0.0262
-7.250 -0.3723 0.01671 0.01024 -0.0942 0.9196 0.0365
-7.000 -0.3405 0.01609 0.00967 -0.0960 0.9183 0.0476
-6.750 -0.3072 0.01542 0.00907 -0.0982 0.9172 0.0640
-6.500 -0.2735 0.01457 0.00841 -0.1008 0.9161 0.1004
-6.250 -0.2632 0.01412 0.00809 -0.0983 0.9091 0.1301
-6.000 -0.2343 0.01334 0.00754 -0.0999 0.9064 0.1824
-5.750 -0.1996 0.01229 0.00686 -0.1029 0.9047 0.2656
-5.500 -0.1598 0.01116 0.00618 -0.1073 0.9037 0.3743
-5.250 -0.1156 0.01016 0.00563 -0.1123 0.9029 0.4807
-5.000 -0.0738 0.00968 0.00542 -0.1159 0.9022 0.5543
-4.750 -0.0336 0.00950 0.00533 -0.1187 0.9012 0.5965
-4.500 -0.0063 0.00954 0.00538 -0.1186 0.8968 0.6167
-4.250 0.0242 0.00951 0.00531 -0.1192 0.8926 0.6308
-4.000 0.0586 0.00949 0.00527 -0.1204 0.8900 0.6434
-3.750 0.0942 0.00946 0.00523 -0.1218 0.8879 0.6521
-3.500 0.1342 0.00939 0.00507 -0.1244 0.8860 0.6610
-3.250 0.1555 0.00951 0.00523 -0.1228 0.8804 0.6661
-3.000 0.1854 0.00954 0.00523 -0.1232 0.8761 0.6729
-2.750 0.2216 0.00946 0.00509 -0.1249 0.8731 0.6784
-2.500 0.2564 0.00943 0.00504 -0.1262 0.8704 0.6815
-2.250 0.2775 0.00951 0.00513 -0.1247 0.8640 0.6854
-2.000 0.3110 0.00944 0.00501 -0.1259 0.8596 0.6901
-1.750 0.3474 0.00934 0.00484 -0.1277 0.8557 0.6939
-1.500 0.3690 0.00940 0.00494 -0.1262 0.8487 0.6966
-1.250 0.3988 0.00941 0.00493 -0.1265 0.8432 0.6996
-1.000 0.4305 0.00939 0.00488 -0.1273 0.8378 0.7029
-0.750 0.4584 0.00933 0.00479 -0.1274 0.8297 0.7069
-0.500 0.4915 0.00928 0.00469 -0.1285 0.8237 0.7098
-0.250 0.5130 0.00935 0.00479 -0.1270 0.8154 0.7120
0.000 0.5437 0.00939 0.00480 -0.1275 0.8094 0.7144
0.250 0.5675 0.00944 0.00488 -0.1266 0.8009 0.7171
0.500 0.5996 0.00944 0.00482 -0.1276 0.7937 0.7203
0.750 0.6277 0.00942 0.00478 -0.1279 0.7838 0.7240
1.000 0.6535 0.00945 0.00479 -0.1274 0.7737 0.7259
1.250 0.6789 0.00952 0.00485 -0.1268 0.7626 0.7278
1.500 0.7019 0.00961 0.00494 -0.1257 0.7504 0.7300
1.750 0.7261 0.00969 0.00500 -0.1249 0.7364 0.7325
2.000 0.7511 0.00977 0.00502 -0.1244 0.7196 0.7353
2.250 0.7773 0.00984 0.00501 -0.1243 0.7011 0.7384
2.500 0.8015 0.00994 0.00503 -0.1237 0.6810 0.7408
2.750 0.8212 0.01009 0.00514 -0.1220 0.6596 0.7424
3.000 0.8396 0.01030 0.00527 -0.1200 0.6365 0.7441
3.250 0.8566 0.01052 0.00541 -0.1179 0.6120 0.7460
3.500 0.8730 0.01080 0.00558 -0.1157 0.5868 0.7483
3.750 0.8903 0.01111 0.00577 -0.1137 0.5587 0.7511
4.000 0.9094 0.01146 0.00599 -0.1123 0.5313 0.7542
4.250 0.9292 0.01183 0.00623 -0.1111 0.5045 0.7565
4.500 0.9465 0.01221 0.00652 -0.1093 0.4801 0.7581
4.750 0.9643 0.01261 0.00684 -0.1075 0.4583 0.7598
5.000 0.9832 0.01298 0.00716 -0.1061 0.4345 0.7617
5.250 1.0000 0.01347 0.00753 -0.1043 0.4103 0.7637
5.500 1.0196 0.01389 0.00787 -0.1032 0.3861 0.7658
5.750 1.0391 0.01436 0.00823 -0.1021 0.3637 0.7681
6.000 1.0599 0.01481 0.00859 -0.1013 0.3459 0.7705
6.250 1.0814 0.01523 0.00895 -0.1007 0.3295 0.7724
6.500 1.1002 0.01563 0.00932 -0.0993 0.3126 0.7740
6.750 1.1179 0.01610 0.00975 -0.0979 0.2961 0.7757
7.000 1.1354 0.01660 0.01020 -0.0964 0.2811 0.7775
7.250 1.1539 0.01709 0.01065 -0.0952 0.2666 0.7795
7.750 1.1926 0.01810 0.01158 -0.0932 0.2389 0.7837
8.000 1.2124 0.01863 0.01208 -0.0925 0.2260 0.7859
8.250 1.2329 0.01918 0.01259 -0.0919 0.2141 0.7880
8.500 1.2496 0.01972 0.01312 -0.0905 0.2020 0.7896
8.750 1.2658 0.02032 0.01369 -0.0890 0.1903 0.7913
9.000 1.2827 0.02090 0.01427 -0.0877 0.1807 0.7932
9.250 1.2988 0.02156 0.01493 -0.0863 0.1723 0.7952
9.500 1.3165 0.02217 0.01555 -0.0852 0.1633 0.7974
9.750 1.3340 0.02283 0.01621 -0.0842 0.1539 0.7996
10.000 1.3504 0.02359 0.01694 -0.0832 0.1439 0.8016
10.250 1.3671 0.02438 0.01769 -0.0823 0.1342 0.8036
10.500 1.3815 0.02513 0.01845 -0.0808 0.1257 0.8053
10.750 1.3936 0.02605 0.01935 -0.0792 0.1162 0.8070
11.000 1.4075 0.02689 0.02020 -0.0778 0.1060 0.8087
11.250 1.4202 0.02785 0.02115 -0.0764 0.0973 0.8105
11.500 1.4316 0.02894 0.02221 -0.0749 0.0890 0.8124
11.750 1.4436 0.03003 0.02330 -0.0736 0.0802 0.8144
12.000 1.4552 0.03119 0.02444 -0.0723 0.0721 0.8164
12.250 1.4646 0.03255 0.02577 -0.0709 0.0636 0.8183
12.500 1.4738 0.03390 0.02713 -0.0696 0.0580 0.8199
12.750 1.4831 0.03520 0.02846 -0.0681 0.0533 0.8215
13.000 1.4913 0.03661 0.02991 -0.0667 0.0478 0.8231
13.250 1.4985 0.03814 0.03147 -0.0652 0.0434 0.8249
13.500 1.5028 0.03999 0.03331 -0.0637 0.0366 0.8269
13.750 1.5083 0.04182 0.03516 -0.0625 0.0327 0.8290
14.000 1.5130 0.04381 0.03718 -0.0613 0.0292 0.8310
14.250 1.5177 0.04587 0.03929 -0.0604 0.0249 0.8328
14.500 1.5210 0.04816 0.04160 -0.0595 0.0193 0.8345
14.750 1.5086 0.05195 0.04536 -0.0579 0.0106 0.8359
15.000 1.5029 0.05522 0.04871 -0.0568 0.0065 0.8373
15.250 1.4968 0.05867 0.05225 -0.0561 0.0050 0.8388
15.500 1.4944 0.06184 0.05553 -0.0556 0.0046 0.8403
15.750 1.4918 0.06514 0.05894 -0.0554 0.0043 0.8420
16.000 1.4885 0.06868 0.06260 -0.0555 0.0041 0.8437
16.250 1.4853 0.07231 0.06635 -0.0557 0.0040 0.8454
16.500 1.4812 0.07616 0.07033 -0.0562 0.0039 0.8472
16.750 1.4754 0.08033 0.07464 -0.0569 0.0039 0.8488
17.000 1.4684 0.08477 0.07921 -0.0578 0.0038 0.8503
17.250 1.4601 0.08938 0.08397 -0.0588 0.0037 0.8518
17.500 1.4511 0.09417 0.08890 -0.0600 0.0037 0.8532
17.750 1.4415 0.09912 0.09400 -0.0615 0.0037 0.8546
18.000 1.4300 0.10448 0.09950 -0.0632 0.0036 0.8560
18.250 1.4169 0.11022 0.10540 -0.0653 0.0036 0.8573
18.500 1.4046 0.11595 0.11127 -0.0676 0.0036 0.8588
18.750 1.3916 0.12190 0.11736 -0.0702 0.0035 0.8603
19.000 1.3782 0.12802 0.12363 -0.0731 0.0035 0.8618
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