FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.24 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-1000000.txt Download as CSV file: xf-fx73cl2152-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL2-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5588 0.05255 0.05003 -0.1071 0.9819 0.0262
-12.000 -0.5724 0.04382 0.04111 -0.1192 0.9767 0.0264
-11.750 -0.5858 0.03727 0.03441 -0.1266 0.9688 0.0265
-11.500 -0.5590 0.03082 0.02777 -0.1402 0.9659 0.0268
-11.250 -0.5310 0.02621 0.02297 -0.1507 0.9610 0.0271
-11.000 -0.4935 0.02335 0.01993 -0.1588 0.9577 0.0275
-10.750 -0.4554 0.02170 0.01814 -0.1637 0.9559 0.0279
-10.500 -0.4164 0.02045 0.01678 -0.1677 0.9544 0.0281
-10.250 -0.3762 0.01839 0.01457 -0.1731 0.9532 0.0288
-10.000 -0.3534 0.01759 0.01375 -0.1730 0.9467 0.0292
-9.750 -0.3188 0.01686 0.01300 -0.1749 0.9431 0.0297
-9.500 -0.2816 0.01608 0.01217 -0.1773 0.9401 0.0302
-9.250 -0.2577 0.01547 0.01151 -0.1769 0.9297 0.0306
-9.000 -0.2209 0.01471 0.01067 -0.1790 0.9211 0.0312
-8.750 -0.1712 0.01390 0.00975 -0.1837 0.9083 0.0318
-8.500 -0.0713 0.01264 0.00816 -0.1991 0.8617 0.0328
-8.250 -0.0351 0.01262 0.00764 -0.2011 0.7580 0.0335
-8.000 -0.0159 0.01272 0.00742 -0.1994 0.6910 0.0340
-7.750 0.0090 0.01270 0.00718 -0.1989 0.6460 0.0347
-7.500 0.0364 0.01261 0.00689 -0.1989 0.6116 0.0353
-7.250 0.0655 0.01246 0.00659 -0.1992 0.5847 0.0360
-7.000 0.0951 0.01234 0.00631 -0.1996 0.5618 0.0365
-6.750 0.1266 0.01204 0.00587 -0.2005 0.5422 0.0372
-6.500 0.1586 0.01175 0.00549 -0.2016 0.5262 0.0382
-6.250 0.1892 0.01162 0.00527 -0.2021 0.5121 0.0390
-6.000 0.2198 0.01149 0.00507 -0.2026 0.5012 0.0400
-5.750 0.2500 0.01141 0.00490 -0.2030 0.4911 0.0410
-5.500 0.2801 0.01132 0.00475 -0.2033 0.4831 0.0417
-5.250 0.3131 0.01103 0.00438 -0.2044 0.4744 0.0432
-5.000 0.3439 0.01089 0.00421 -0.2049 0.4690 0.0444
-4.750 0.3742 0.01080 0.00407 -0.2053 0.4633 0.0457
-4.500 0.4040 0.01076 0.00395 -0.2055 0.4572 0.0469
-4.250 0.4357 0.01058 0.00374 -0.2062 0.4525 0.0490
-4.000 0.4661 0.01049 0.00363 -0.2066 0.4487 0.0510
-3.750 0.4960 0.01045 0.00354 -0.2068 0.4449 0.0529
-3.500 0.5271 0.01033 0.00340 -0.2074 0.4409 0.0560
-3.250 0.5568 0.01033 0.00334 -0.2076 0.4364 0.0591
-3.000 0.5877 0.01023 0.00325 -0.2080 0.4338 0.0640
-2.750 0.6185 0.01013 0.00317 -0.2085 0.4314 0.0711
-2.500 0.6496 0.01003 0.00309 -0.2090 0.4286 0.0847
-2.250 0.6817 0.00987 0.00305 -0.2099 0.4257 0.1210
-2.000 0.7120 0.00984 0.00307 -0.2102 0.4226 0.1491
-1.750 0.7414 0.00988 0.00312 -0.2104 0.4187 0.1677
-1.500 0.7704 0.00992 0.00316 -0.2104 0.4157 0.1805
-1.250 0.8001 0.00991 0.00319 -0.2106 0.4140 0.1935
-1.000 0.8294 0.00992 0.00322 -0.2107 0.4121 0.2045
-0.750 0.8585 0.00994 0.00325 -0.2107 0.4099 0.2155
-0.500 0.8876 0.00997 0.00330 -0.2108 0.4074 0.2277
-0.250 0.9162 0.01003 0.00335 -0.2107 0.4049 0.2380
0.000 0.9449 0.01010 0.00342 -0.2107 0.4020 0.2517
0.250 0.9734 0.01022 0.00354 -0.2107 0.3986 0.2685
0.500 1.0025 0.01025 0.00362 -0.2108 0.3970 0.2876
0.750 1.0317 0.01027 0.00369 -0.2109 0.3957 0.3068
1.000 1.0606 0.01030 0.00376 -0.2109 0.3941 0.3248
1.250 1.0895 0.01033 0.00384 -0.2110 0.3924 0.3447
1.500 1.1182 0.01038 0.00393 -0.2110 0.3905 0.3672
1.750 1.1467 0.01044 0.00403 -0.2110 0.3885 0.3905
2.000 1.1749 0.01052 0.00414 -0.2109 0.3862 0.4127
2.250 1.2028 0.01063 0.00426 -0.2107 0.3836 0.4360
2.750 1.2588 0.01085 0.00457 -0.2106 0.3788 0.4853
3.000 1.2871 0.01090 0.00468 -0.2105 0.3774 0.5106
3.250 1.3151 0.01096 0.00480 -0.2104 0.3757 0.5374
3.500 1.3429 0.01102 0.00492 -0.2102 0.3738 0.5626
3.750 1.3704 0.01110 0.00505 -0.2100 0.3718 0.5864
4.000 1.3975 0.01120 0.00519 -0.2097 0.3697 0.6109
4.250 1.4241 0.01132 0.00534 -0.2094 0.3673 0.6365
4.500 1.4503 0.01148 0.00553 -0.2090 0.3644 0.6610
4.750 1.4767 0.01165 0.00574 -0.2086 0.3616 0.6867
5.000 1.5035 0.01169 0.00587 -0.2082 0.3601 0.7161
5.250 1.5300 0.01175 0.00602 -0.2079 0.3581 0.7492
5.500 1.5562 0.01182 0.00618 -0.2074 0.3559 0.7839
5.750 1.5814 0.01189 0.00635 -0.2068 0.3535 0.8284
6.000 1.5935 0.01178 0.00643 -0.2033 0.3512 0.9644
6.250 1.6186 0.01197 0.00660 -0.2027 0.3483 1.0000
6.500 1.6429 0.01224 0.00683 -0.2020 0.3449 1.0000
6.750 1.6688 0.01234 0.00697 -0.2015 0.3432 1.0000
7.000 1.6943 0.01247 0.00712 -0.2010 0.3407 1.0000
7.250 1.7193 0.01262 0.00728 -0.2004 0.3378 1.0000
7.500 1.7435 0.01280 0.00746 -0.1996 0.3348 1.0000
7.750 1.7663 0.01305 0.00768 -0.1987 0.3309 1.0000
8.000 1.7898 0.01325 0.00789 -0.1978 0.3269 1.0000
8.250 1.8142 0.01339 0.00805 -0.1971 0.3222 1.0000
8.500 1.8364 0.01363 0.00826 -0.1961 0.3164 1.0000
8.750 1.8582 0.01391 0.00853 -0.1950 0.3113 1.0000
9.000 1.8817 0.01411 0.00875 -0.1942 0.3070 1.0000
9.250 1.9037 0.01438 0.00902 -0.1931 0.3022 1.0000
9.500 1.9238 0.01475 0.00936 -0.1918 0.2965 1.0000
9.750 1.9464 0.01499 0.00963 -0.1909 0.2926 1.0000
10.000 1.9672 0.01530 0.00996 -0.1896 0.2883 1.0000
10.250 1.9864 0.01570 0.01034 -0.1882 0.2836 1.0000
10.500 2.0063 0.01606 0.01072 -0.1868 0.2794 1.0000
10.750 2.0268 0.01639 0.01108 -0.1856 0.2752 1.0000
11.000 2.0453 0.01682 0.01151 -0.1841 0.2707 1.0000
11.250 2.0615 0.01735 0.01204 -0.1822 0.2658 1.0000
11.500 2.0813 0.01771 0.01245 -0.1810 0.2626 1.0000
11.750 2.0994 0.01816 0.01292 -0.1795 0.2583 1.0000
12.000 2.1144 0.01876 0.01352 -0.1775 0.2533 1.0000
12.250 2.1303 0.01932 0.01411 -0.1757 0.2485 1.0000
12.500 2.1470 0.01984 0.01467 -0.1741 0.2438 1.0000
12.750 2.1598 0.02057 0.01540 -0.1719 0.2382 1.0000
13.000 2.1736 0.02127 0.01612 -0.1699 0.2331 1.0000
13.250 2.1868 0.02200 0.01688 -0.1679 0.2271 1.0000
13.500 2.1951 0.02304 0.01791 -0.1654 0.2198 1.0000
13.750 2.2062 0.02393 0.01883 -0.1632 0.2122 1.0000
14.000 2.2112 0.02522 0.02011 -0.1604 0.2030 1.0000
14.250 2.2120 0.02686 0.02171 -0.1573 0.1915 1.0000
14.500 2.2088 0.02885 0.02367 -0.1540 0.1784 1.0000
15.000 2.1865 0.03450 0.02926 -0.1471 0.1518 1.0000
15.250 2.1720 0.03801 0.03278 -0.1442 0.1410 1.0000
15.500 2.1574 0.04187 0.03668 -0.1420 0.1326 1.0000
15.750 2.1384 0.04662 0.04148 -0.1404 0.1253 1.0000
16.000 2.1228 0.05140 0.04633 -0.1395 0.1192 1.0000
16.500 2.0819 0.06330 0.05842 -0.1396 0.1096 1.0000
16.750 2.0569 0.07034 0.06556 -0.1403 0.1056 1.0000
17.000 2.0310 0.07776 0.07309 -0.1415 0.1019 1.0000
17.250 2.0104 0.08455 0.08000 -0.1427 0.0988 1.0000
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