FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.61 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-1000000-n5.txt Download as CSV file: xf-fx73cl3152-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL3-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1697 0.05642 0.05333 -0.1431 0.8131 0.0206
-11.500 -0.2365 0.04634 0.04310 -0.1490 0.8053 0.0207
-11.250 -0.2903 0.03794 0.03457 -0.1554 0.7967 0.0206
-11.000 -0.3106 0.02810 0.02447 -0.1687 0.7882 0.0208
-10.750 -0.2929 0.02069 0.01673 -0.1811 0.7753 0.0209
-10.500 -0.2676 0.01891 0.01472 -0.1838 0.7550 0.0211
-10.250 -0.2449 0.01796 0.01350 -0.1845 0.7138 0.0214
-10.000 -0.2224 0.01727 0.01254 -0.1847 0.6729 0.0215
-9.750 -0.1983 0.01670 0.01174 -0.1849 0.6426 0.0217
-9.500 -0.1733 0.01616 0.01101 -0.1850 0.6170 0.0218
-9.250 -0.1479 0.01569 0.01036 -0.1851 0.5939 0.0219
-9.000 -0.1225 0.01510 0.00961 -0.1853 0.5734 0.0222
-8.750 -0.0963 0.01464 0.00903 -0.1853 0.5568 0.0225
-8.500 -0.0698 0.01429 0.00856 -0.1853 0.5423 0.0228
-8.250 -0.0432 0.01398 0.00814 -0.1852 0.5296 0.0230
-8.000 -0.0161 0.01369 0.00776 -0.1851 0.5183 0.0233
-7.750 0.0109 0.01342 0.00739 -0.1849 0.5082 0.0236
-7.500 0.0381 0.01316 0.00704 -0.1848 0.4987 0.0240
-7.250 0.0652 0.01293 0.00671 -0.1846 0.4903 0.0243
-7.000 0.0926 0.01269 0.00640 -0.1844 0.4828 0.0246
-6.750 0.1197 0.01251 0.00611 -0.1842 0.4747 0.0250
-6.500 0.1473 0.01231 0.00584 -0.1840 0.4684 0.0252
-6.250 0.1746 0.01208 0.00554 -0.1838 0.4617 0.0256
-6.000 0.2017 0.01189 0.00528 -0.1835 0.4556 0.0262
-5.750 0.2293 0.01172 0.00507 -0.1833 0.4514 0.0267
-5.500 0.2570 0.01157 0.00488 -0.1831 0.4472 0.0272
-5.250 0.2845 0.01145 0.00470 -0.1828 0.4429 0.0278
-5.000 0.3119 0.01135 0.00454 -0.1825 0.4385 0.0284
-4.750 0.3394 0.01126 0.00439 -0.1822 0.4347 0.0290
-4.500 0.3670 0.01109 0.00420 -0.1820 0.4320 0.0297
-4.250 0.3946 0.01098 0.00406 -0.1817 0.4289 0.0304
-4.000 0.4221 0.01089 0.00393 -0.1814 0.4254 0.0312
-3.750 0.4494 0.01083 0.00383 -0.1811 0.4218 0.0320
-3.500 0.4765 0.01079 0.00373 -0.1807 0.4182 0.0328
-3.250 0.5040 0.01070 0.00362 -0.1804 0.4159 0.0338
-3.000 0.5316 0.01062 0.00353 -0.1801 0.4141 0.0350
-2.750 0.5591 0.01057 0.00346 -0.1798 0.4120 0.0363
-2.500 0.5865 0.01053 0.00339 -0.1795 0.4098 0.0377
-2.250 0.6137 0.01047 0.00333 -0.1792 0.4075 0.0394
-2.000 0.6407 0.01046 0.00329 -0.1788 0.4050 0.0411
-1.750 0.6676 0.01045 0.00325 -0.1784 0.4024 0.0429
-1.500 0.6942 0.01045 0.00323 -0.1779 0.3995 0.0455
-1.250 0.7214 0.01042 0.00320 -0.1776 0.3979 0.0483
-1.000 0.7486 0.01039 0.00318 -0.1772 0.3966 0.0518
-0.750 0.7756 0.01037 0.00317 -0.1768 0.3951 0.0559
-0.500 0.8025 0.01036 0.00316 -0.1765 0.3933 0.0618
-0.250 0.8291 0.01034 0.00316 -0.1760 0.3912 0.0706
0.000 0.8556 0.01034 0.00318 -0.1756 0.3890 0.0825
0.250 0.8817 0.01034 0.00321 -0.1751 0.3869 0.0964
0.500 0.9077 0.01037 0.00325 -0.1746 0.3844 0.1118
0.750 0.9332 0.01041 0.00331 -0.1740 0.3816 0.1268
1.000 0.9596 0.01042 0.00336 -0.1735 0.3801 0.1417
1.250 0.9860 0.01044 0.00341 -0.1731 0.3788 0.1564
1.500 1.0122 0.01046 0.00347 -0.1726 0.3770 0.1707
1.750 1.0381 0.01050 0.00354 -0.1721 0.3752 0.1860
2.000 1.0638 0.01055 0.00361 -0.1715 0.3733 0.2015
2.250 1.0891 0.01060 0.00370 -0.1709 0.3714 0.2217
2.500 1.1142 0.01066 0.00380 -0.1703 0.3696 0.2390
2.750 1.1390 0.01075 0.00389 -0.1696 0.3677 0.2537
3.000 1.1633 0.01084 0.00401 -0.1688 0.3655 0.2695
3.250 1.1877 0.01093 0.00412 -0.1680 0.3636 0.2853
3.500 1.2127 0.01099 0.00422 -0.1674 0.3623 0.3018
3.750 1.2371 0.01104 0.00433 -0.1666 0.3609 0.3227
4.000 1.2605 0.01111 0.00444 -0.1657 0.3592 0.3430
4.250 1.2831 0.01118 0.00456 -0.1646 0.3575 0.3671
4.500 1.3055 0.01126 0.00469 -0.1635 0.3557 0.3900
4.750 1.3278 0.01136 0.00483 -0.1624 0.3538 0.4135
5.000 1.3498 0.01149 0.00499 -0.1612 0.3518 0.4380
5.250 1.3712 0.01162 0.00518 -0.1600 0.3498 0.4668
5.500 1.3923 0.01178 0.00538 -0.1587 0.3476 0.4982
5.750 1.4149 0.01187 0.00557 -0.1577 0.3464 0.5348
6.000 1.4373 0.01198 0.00576 -0.1567 0.3448 0.5659
6.250 1.4595 0.01210 0.00595 -0.1557 0.3429 0.5994
6.500 1.4812 0.01223 0.00616 -0.1546 0.3407 0.6355
6.750 1.5023 0.01238 0.00638 -0.1534 0.3381 0.6723
7.000 1.5230 0.01254 0.00661 -0.1522 0.3359 0.7186
7.500 1.6578 0.01289 0.00731 -0.1697 0.3300 1.0000
7.750 1.6816 0.01309 0.00753 -0.1692 0.3281 1.0000
8.000 1.7049 0.01332 0.00777 -0.1685 0.3258 1.0000
8.250 1.7277 0.01357 0.00803 -0.1678 0.3232 1.0000
8.500 1.7494 0.01387 0.00832 -0.1670 0.3202 1.0000
8.750 1.7703 0.01421 0.00865 -0.1661 0.3171 1.0000
9.000 1.7920 0.01451 0.00897 -0.1653 0.3147 1.0000
9.250 1.8140 0.01479 0.00927 -0.1646 0.3126 1.0000
9.500 1.8355 0.01510 0.00960 -0.1638 0.3102 1.0000
9.750 1.8562 0.01545 0.00998 -0.1629 0.3073 1.0000
10.000 1.8758 0.01586 0.01039 -0.1619 0.3045 1.0000
10.250 1.8945 0.01632 0.01085 -0.1608 0.3015 1.0000
10.500 1.9142 0.01672 0.01128 -0.1599 0.2990 1.0000
10.750 1.9340 0.01712 0.01171 -0.1590 0.2959 1.0000
11.000 1.9522 0.01762 0.01222 -0.1579 0.2917 1.0000
11.500 1.9843 0.01886 0.01345 -0.1553 0.2802 1.0000
11.750 1.9988 0.01958 0.01417 -0.1539 0.2744 1.0000
12.000 2.0127 0.02035 0.01494 -0.1524 0.2696 1.0000
12.250 2.0288 0.02099 0.01560 -0.1512 0.2655 1.0000
12.500 2.0422 0.02181 0.01644 -0.1497 0.2609 1.0000
12.750 2.0545 0.02270 0.01734 -0.1482 0.2570 1.0000
13.000 2.0683 0.02351 0.01818 -0.1469 0.2541 1.0000
13.250 2.0820 0.02433 0.01905 -0.1456 0.2505 1.0000
13.500 2.0943 0.02526 0.02002 -0.1442 0.2473 1.0000
13.750 2.1031 0.02645 0.02122 -0.1425 0.2434 1.0000
14.000 2.1128 0.02759 0.02239 -0.1410 0.2392 1.0000
14.250 2.1218 0.02880 0.02364 -0.1394 0.2343 1.0000
14.500 2.1235 0.03062 0.02546 -0.1374 0.2276 1.0000
14.750 2.1311 0.03203 0.02690 -0.1359 0.2221 1.0000
15.000 2.1316 0.03407 0.02896 -0.1341 0.2153 1.0000
15.250 2.1337 0.03608 0.03099 -0.1325 0.2096 1.0000
15.500 2.1306 0.03865 0.03358 -0.1308 0.2015 1.0000
15.750 2.1256 0.04151 0.03647 -0.1292 0.1936 1.0000
16.000 2.1127 0.04532 0.04029 -0.1275 0.1843 1.0000
16.250 2.0954 0.04980 0.04479 -0.1260 0.1742 1.0000
16.500 2.0737 0.05495 0.04997 -0.1248 0.1643 1.0000
16.750 2.0464 0.06093 0.05599 -0.1237 0.1551 1.0000
17.250 1.9901 0.07355 0.06874 -0.1224 0.1408 1.0000
17.500 1.9599 0.08029 0.07554 -0.1221 0.1348 1.0000
17.750 1.9335 0.08664 0.08195 -0.1220 0.1285 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 73-CL3-152 (fx73cl3152-il)