FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 200,000 Max Cl/Cd: 63.96 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-200000.txt Download as CSV file: xf-fx73cl3152-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.1049 0.10690 0.10325 -0.0999 0.9494 0.0562
-9.750 0.1249 0.10332 0.09965 -0.1052 0.9454 0.0584
-9.500 0.1379 0.09962 0.09594 -0.1132 0.9415 0.0596
-9.250 0.1643 0.09591 0.09222 -0.1143 0.9355 0.0603
-9.000 0.1878 0.09280 0.08909 -0.1172 0.9287 0.0615
-8.750 0.2141 0.08936 0.08561 -0.1222 0.9232 0.0636
-8.500 0.2051 0.08796 0.08420 -0.1267 0.9096 0.0662
-8.250 0.2212 0.08452 0.08075 -0.1278 0.9002 0.0668
-8.000 0.2452 0.08162 0.07781 -0.1276 0.8898 0.0677
-7.750 0.2566 0.07972 0.07589 -0.1271 0.8765 0.0691
-7.500 0.2653 0.07776 0.07390 -0.1275 0.8626 0.0717
-7.250 0.2665 0.06419 0.06041 -0.1168 0.7808 0.0749
-7.000 0.2620 0.07348 0.06957 -0.1286 0.8302 0.0749
-6.750 0.2749 0.07155 0.06760 -0.1268 0.8093 0.0759
-6.500 0.2815 0.06989 0.06590 -0.1251 0.7812 0.0772
-6.250 0.2858 0.06818 0.06407 -0.1241 0.7454 0.0791
-6.000 0.2573 0.06618 0.06195 -0.1303 0.7145 0.0829
-5.750 0.2720 0.06420 0.05970 -0.1261 0.6828 0.0836
-5.500 0.2852 0.06279 0.05808 -0.1236 0.6568 0.0845
-5.250 0.2965 0.06144 0.05657 -0.1226 0.6374 0.0861
-5.000 0.3062 0.05983 0.05483 -0.1233 0.6223 0.0889
-4.750 0.3143 0.05595 0.05086 -0.1317 0.6114 0.0936
-4.500 0.3601 0.02774 0.02127 -0.1752 0.6103 0.0661
-4.250 0.3882 0.02486 0.01790 -0.1776 0.5983 0.0658
-4.000 0.4166 0.02281 0.01522 -0.1792 0.5884 0.0667
-3.750 0.4418 0.02214 0.01461 -0.1790 0.5784 0.0686
-3.500 0.4693 0.02139 0.01355 -0.1793 0.5705 0.0705
-3.250 0.4971 0.02038 0.01221 -0.1795 0.5630 0.0723
-3.000 0.5251 0.01969 0.01112 -0.1795 0.5561 0.0740
-2.750 0.5523 0.01917 0.01052 -0.1795 0.5503 0.0770
-2.500 0.5792 0.01883 0.01009 -0.1793 0.5442 0.0806
-2.250 0.6063 0.01834 0.00945 -0.1790 0.5384 0.0839
-2.000 0.6336 0.01811 0.00917 -0.1788 0.5333 0.0881
-1.750 0.6615 0.01792 0.00883 -0.1787 0.5288 0.0939
-1.500 0.6882 0.01773 0.00870 -0.1784 0.5242 0.1005
-1.250 0.7153 0.01752 0.00849 -0.1781 0.5199 0.1086
-1.000 0.7428 0.01742 0.00836 -0.1779 0.5159 0.1210
-0.750 0.7714 0.01744 0.00832 -0.1779 0.5121 0.1389
-0.500 0.7983 0.01740 0.00835 -0.1776 0.5083 0.1641
-0.250 0.8248 0.01745 0.00847 -0.1773 0.5044 0.1912
0.000 0.8520 0.01757 0.00858 -0.1771 0.5008 0.2165
0.250 0.8794 0.01768 0.00870 -0.1769 0.4975 0.2394
0.500 0.9073 0.01785 0.00884 -0.1768 0.4943 0.2618
0.750 0.9353 0.01811 0.00908 -0.1768 0.4911 0.2845
1.000 0.9605 0.01822 0.00929 -0.1762 0.4878 0.3079
1.250 0.9865 0.01837 0.00950 -0.1758 0.4845 0.3330
1.500 1.0131 0.01852 0.00967 -0.1755 0.4813 0.3587
1.750 1.0401 0.01865 0.00984 -0.1752 0.4783 0.3848
2.000 1.0681 0.01885 0.01003 -0.1751 0.4753 0.4154
2.250 1.0962 0.01919 0.01041 -0.1752 0.4724 0.4487
2.500 1.1200 0.01932 0.01071 -0.1744 0.4696 0.4851
2.750 1.1441 0.01949 0.01102 -0.1736 0.4664 0.5262
3.000 1.1693 0.01967 0.01131 -0.1731 0.4633 0.5730
3.250 1.1959 0.01985 0.01158 -0.1728 0.4605 0.6237
3.500 1.2249 0.02004 0.01181 -0.1729 0.4578 0.6826
3.750 1.2586 0.02016 0.01204 -0.1741 0.4551 0.7736
4.000 1.2917 0.02039 0.01240 -0.1754 0.4521 1.0000
4.250 1.3158 0.02074 0.01277 -0.1749 0.4491 1.0000
4.500 1.3407 0.02112 0.01313 -0.1744 0.4461 1.0000
4.750 1.3665 0.02148 0.01346 -0.1742 0.4433 1.0000
5.000 1.3933 0.02184 0.01375 -0.1740 0.4407 1.0000
5.250 1.4213 0.02222 0.01403 -0.1741 0.4382 1.0000
5.500 1.4508 0.02283 0.01452 -0.1746 0.4355 1.0000
5.750 1.4716 0.02325 0.01503 -0.1735 0.4328 1.0000
6.000 1.4927 0.02368 0.01553 -0.1725 0.4297 1.0000
6.250 1.5153 0.02412 0.01601 -0.1717 0.4267 1.0000
6.500 1.5394 0.02452 0.01641 -0.1712 0.4240 1.0000
6.750 1.5654 0.02490 0.01676 -0.1710 0.4215 1.0000
7.000 1.5933 0.02533 0.01711 -0.1711 0.4192 1.0000
7.250 1.6214 0.02605 0.01777 -0.1714 0.4167 1.0000
7.500 1.6375 0.02658 0.01847 -0.1697 0.4140 1.0000
7.750 1.6550 0.02713 0.01912 -0.1682 0.4107 1.0000
8.000 1.6749 0.02760 0.01965 -0.1671 0.4076 1.0000
8.250 1.6975 0.02801 0.02006 -0.1664 0.4048 1.0000
8.500 1.7234 0.02839 0.02043 -0.1662 0.4024 1.0000
8.750 1.7524 0.02887 0.02084 -0.1666 0.4002 1.0000
9.000 1.7727 0.02968 0.02172 -0.1658 0.3976 1.0000
9.250 1.7828 0.03046 0.02268 -0.1633 0.3947 1.0000
9.500 1.7959 0.03117 0.02352 -0.1612 0.3915 1.0000
9.750 1.8130 0.03172 0.02412 -0.1598 0.3886 1.0000
10.000 1.8344 0.03211 0.02453 -0.1590 0.3860 1.0000
10.250 1.8616 0.03246 0.02486 -0.1591 0.3838 1.0000
10.500 1.8935 0.03304 0.02537 -0.1601 0.3816 1.0000
10.750 1.8953 0.03417 0.02671 -0.1565 0.3789 1.0000
11.000 1.8946 0.03530 0.02805 -0.1527 0.3759 1.0000
11.250 1.8969 0.03624 0.02911 -0.1492 0.3729 1.0000
11.500 1.9082 0.03687 0.02980 -0.1470 0.3703 1.0000
11.750 1.9278 0.03728 0.03023 -0.1460 0.3680 1.0000
12.000 1.9585 0.03756 0.03051 -0.1467 0.3660 1.0000
12.250 1.9930 0.03818 0.03109 -0.1482 0.3638 1.0000
12.500 1.9516 0.04046 0.03368 -0.1393 0.3608 1.0000
12.750 1.9243 0.04289 0.03634 -0.1333 0.3574 1.0000
13.000 1.9181 0.04461 0.03818 -0.1300 0.3544 1.0000
13.250 1.9402 0.04464 0.03822 -0.1294 0.3517 1.0000
13.500 2.0050 0.04222 0.03561 -0.1329 0.3486 1.0000
13.750 1.9795 0.04479 0.03837 -0.1277 0.3450 1.0000
14.000 1.9118 0.05069 0.04459 -0.1204 0.3407 1.0000
14.250 1.9094 0.05244 0.04643 -0.1184 0.3371 1.0000
14.500 1.9487 0.05100 0.04495 -0.1188 0.3346 1.0000
14.750 2.0121 0.04818 0.04200 -0.1210 0.3323 1.0000
15.000 1.6433 0.09024 0.08486 -0.1133 0.3156 1.0000
15.250 1.6915 0.08618 0.08081 -0.1121 0.3152 1.0000
15.500 1.7458 0.08148 0.07613 -0.1109 0.3148 1.0000
15.750 1.8104 0.07579 0.07042 -0.1099 0.3144 1.0000
16.000 1.9217 0.06543 0.05994 -0.1098 0.3147 1.0000
16.750 1.8378 0.08280 0.07767 -0.1083 0.3003 1.0000
17.000 1.3475 0.16796 0.16312 -0.1370 0.2319 1.0000
17.250 1.3698 0.16706 0.16226 -0.1361 0.2305 1.0000
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