FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 200,000 Max Cl/Cd: 71.01 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-200000-n5.txt Download as CSV file: xf-fx73cl3152-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.1797 0.09554 0.09123 -0.1185 0.8608 0.0449
-9.500 0.1884 0.09309 0.08874 -0.1196 0.8514 0.0456
-9.000 0.1905 0.08587 0.08146 -0.1221 0.8318 0.0371
-8.750 0.1987 0.08384 0.07941 -0.1220 0.8191 0.0366
-8.500 0.2047 0.08146 0.07701 -0.1223 0.8049 0.0364
-8.250 0.2050 0.07861 0.07413 -0.1231 0.7880 0.0370
-8.000 0.2072 0.07600 0.07146 -0.1234 0.7633 0.0370
-7.750 0.2133 0.07394 0.06924 -0.1231 0.7267 0.0368
-7.500 0.2158 0.07185 0.06692 -0.1225 0.6892 0.0365
-7.250 0.2165 0.06967 0.06457 -0.1220 0.6611 0.0363
-7.000 0.2160 0.06739 0.06217 -0.1216 0.6389 0.0361
-6.750 0.2136 0.06501 0.05970 -0.1211 0.6215 0.0360
-6.250 0.1658 0.02526 0.01865 -0.1736 0.6207 0.0377
-6.000 0.1907 0.02425 0.01739 -0.1744 0.6026 0.0383
-5.750 0.2162 0.02319 0.01603 -0.1752 0.5871 0.0389
-5.500 0.2423 0.02213 0.01467 -0.1759 0.5734 0.0397
-5.250 0.2686 0.02114 0.01336 -0.1765 0.5621 0.0407
-5.000 0.2949 0.02026 0.01211 -0.1767 0.5516 0.0418
-4.750 0.3211 0.01975 0.01148 -0.1767 0.5423 0.0429
-4.500 0.3469 0.01940 0.01101 -0.1765 0.5336 0.0441
-4.250 0.3733 0.01896 0.01039 -0.1764 0.5260 0.0455
-4.000 0.3998 0.01848 0.00970 -0.1762 0.5182 0.0469
-3.750 0.4255 0.01813 0.00921 -0.1758 0.5116 0.0480
-3.500 0.4521 0.01784 0.00888 -0.1756 0.5052 0.0495
-3.250 0.4786 0.01759 0.00853 -0.1753 0.4994 0.0516
-3.000 0.5049 0.01737 0.00817 -0.1750 0.4944 0.0537
-2.750 0.5314 0.01718 0.00793 -0.1747 0.4899 0.0558
-2.500 0.5583 0.01698 0.00766 -0.1744 0.4855 0.0584
-2.250 0.5849 0.01681 0.00745 -0.1742 0.4811 0.0612
-2.000 0.6113 0.01672 0.00727 -0.1738 0.4770 0.0650
-1.500 0.6646 0.01654 0.00697 -0.1731 0.4695 0.0742
-1.250 0.6914 0.01645 0.00688 -0.1729 0.4657 0.0810
-1.000 0.7180 0.01639 0.00681 -0.1725 0.4623 0.0903
-0.750 0.7446 0.01637 0.00677 -0.1722 0.4592 0.1032
-0.500 0.7711 0.01639 0.00678 -0.1719 0.4564 0.1198
-0.250 0.7978 0.01645 0.00681 -0.1716 0.4537 0.1393
0.000 0.8244 0.01647 0.00688 -0.1712 0.4507 0.1590
0.250 0.8508 0.01653 0.00695 -0.1709 0.4476 0.1780
0.500 0.8771 0.01661 0.00705 -0.1705 0.4445 0.1970
0.750 0.9034 0.01671 0.00715 -0.1701 0.4418 0.2162
1.000 0.9296 0.01683 0.00726 -0.1697 0.4393 0.2367
1.250 0.9560 0.01697 0.00739 -0.1694 0.4369 0.2582
1.500 0.9825 0.01712 0.00753 -0.1690 0.4344 0.2788
1.750 1.0083 0.01721 0.00769 -0.1686 0.4318 0.2986
2.000 1.0341 0.01733 0.00786 -0.1681 0.4291 0.3197
2.250 1.0599 0.01746 0.00804 -0.1677 0.4265 0.3426
2.500 1.0855 0.01759 0.00822 -0.1672 0.4239 0.3675
2.750 1.1108 0.01775 0.00839 -0.1667 0.4214 0.3950
3.000 1.1366 0.01793 0.00859 -0.1663 0.4190 0.4244
3.250 1.1631 0.01816 0.00881 -0.1661 0.4167 0.4576
3.500 1.1882 0.01830 0.00908 -0.1656 0.4143 0.4935
3.750 1.2140 0.01847 0.00936 -0.1652 0.4117 0.5328
4.000 1.2402 0.01865 0.00963 -0.1649 0.4092 0.5752
4.250 1.2663 0.01883 0.00989 -0.1646 0.4068 0.6196
4.500 1.2926 0.01900 0.01013 -0.1644 0.4043 0.6684
4.750 1.3203 0.01914 0.01034 -0.1645 0.4020 0.7304
5.000 1.3543 0.01918 0.01052 -0.1659 0.3997 1.0000
5.250 1.3793 0.01950 0.01082 -0.1655 0.3976 1.0000
5.500 1.4028 0.01980 0.01114 -0.1648 0.3954 1.0000
5.750 1.4262 0.02012 0.01147 -0.1641 0.3931 1.0000
6.000 1.4492 0.02043 0.01179 -0.1634 0.3906 1.0000
6.250 1.4721 0.02074 0.01209 -0.1626 0.3881 1.0000
6.500 1.4948 0.02105 0.01239 -0.1618 0.3858 1.0000
6.750 1.5182 0.02138 0.01267 -0.1611 0.3835 1.0000
7.000 1.5430 0.02175 0.01298 -0.1608 0.3815 1.0000
7.250 1.5637 0.02212 0.01341 -0.1597 0.3794 1.0000
7.500 1.5829 0.02250 0.01386 -0.1584 0.3771 1.0000
7.750 1.6017 0.02289 0.01431 -0.1570 0.3746 1.0000
8.000 1.6205 0.02328 0.01474 -0.1557 0.3722 1.0000
8.250 1.6395 0.02367 0.01516 -0.1544 0.3700 1.0000
8.500 1.6586 0.02405 0.01555 -0.1531 0.3678 1.0000
8.750 1.6791 0.02444 0.01592 -0.1521 0.3656 1.0000
9.000 1.6994 0.02488 0.01635 -0.1512 0.3634 1.0000
9.250 1.7126 0.02543 0.01703 -0.1491 0.3608 1.0000
9.500 1.7274 0.02598 0.01769 -0.1474 0.3583 1.0000
9.750 1.7426 0.02654 0.01832 -0.1458 0.3557 1.0000
10.000 1.7582 0.02710 0.01893 -0.1443 0.3534 1.0000
10.250 1.7743 0.02764 0.01951 -0.1429 0.3512 1.0000
10.500 1.7922 0.02815 0.02004 -0.1418 0.3491 1.0000
10.750 1.8102 0.02870 0.02059 -0.1407 0.3470 1.0000
11.000 1.8179 0.02961 0.02167 -0.1385 0.3441 1.0000
11.250 1.8276 0.03050 0.02267 -0.1365 0.3413 1.0000
11.500 1.8387 0.03136 0.02363 -0.1348 0.3387 1.0000
11.750 1.8506 0.03219 0.02454 -0.1332 0.3363 1.0000
12.000 1.8644 0.03295 0.02533 -0.1319 0.3342 1.0000
12.250 1.8807 0.03360 0.02599 -0.1308 0.3321 1.0000
12.500 1.8875 0.03481 0.02733 -0.1289 0.3295 1.0000
12.750 1.8901 0.03630 0.02898 -0.1268 0.3264 1.0000
13.000 1.8951 0.03770 0.03050 -0.1249 0.3236 1.0000
13.250 1.9019 0.03901 0.03191 -0.1233 0.3210 1.0000
13.500 1.9115 0.04012 0.03307 -0.1220 0.3184 1.0000
13.750 1.9233 0.04104 0.03398 -0.1208 0.3153 1.0000
14.000 1.9102 0.04395 0.03712 -0.1183 0.3106 1.0000
14.250 1.9051 0.04635 0.03962 -0.1165 0.3057 1.0000
14.500 1.9123 0.04771 0.04097 -0.1154 0.3016 1.0000
14.750 1.9042 0.05077 0.04418 -0.1140 0.2974 1.0000
15.000 1.8933 0.05434 0.04793 -0.1128 0.2931 1.0000
15.250 1.8905 0.05714 0.05081 -0.1120 0.2893 1.0000
15.500 1.8982 0.05877 0.05244 -0.1113 0.2861 1.0000
15.750 1.8792 0.06374 0.05761 -0.1107 0.2819 1.0000
16.000 1.8575 0.06927 0.06330 -0.1105 0.2772 1.0000
16.250 1.8555 0.07230 0.06638 -0.1102 0.2733 1.0000
16.500 1.8615 0.07428 0.06838 -0.1098 0.2700 1.0000
16.750 1.8077 0.08464 0.07902 -0.1108 0.2636 1.0000
17.000 1.8014 0.08846 0.08290 -0.1109 0.2591 1.0000
17.250 1.8216 0.08846 0.08286 -0.1103 0.2561 1.0000
17.500 1.7415 0.10337 0.09807 -0.1132 0.2475 1.0000
17.750 1.7533 0.10461 0.09933 -0.1131 0.2437 1.0000
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Polar data table (+)
Polar graphs
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