FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 100,000 Max Cl/Cd: 50.46 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-100000-n5.txt Download as CSV file: xf-fx73cl3152-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 0.1713 0.09372 0.08838 -0.1108 0.8698 0.0753
-8.250 0.1811 0.09146 0.08612 -0.1107 0.8569 0.0761
-8.000 0.1926 0.08904 0.08369 -0.1115 0.8448 0.0772
-7.750 0.2015 0.08672 0.08134 -0.1122 0.8310 0.0777
-7.500 0.2062 0.08468 0.07931 -0.1120 0.8146 0.0781
-7.250 0.1935 0.08012 0.07471 -0.1134 0.7983 0.0587
-7.000 0.2013 0.07797 0.07254 -0.1127 0.7785 0.0576
-6.750 0.2048 0.07569 0.07023 -0.1125 0.7566 0.0573
-6.500 0.2071 0.07342 0.06789 -0.1124 0.7324 0.0573
-6.250 0.2102 0.07104 0.06539 -0.1125 0.7099 0.0571
-6.000 0.2138 0.06856 0.06278 -0.1130 0.6894 0.0566
-5.750 0.2184 0.06573 0.05982 -0.1144 0.6710 0.0556
-5.500 0.2218 0.06222 0.05619 -0.1170 0.6551 0.0545
-5.000 0.2379 0.05160 0.04530 -0.1295 0.6300 0.0533
-4.750 0.2568 0.05045 0.04405 -0.1303 0.6160 0.0545
-4.500 0.3092 0.03241 0.02495 -0.1624 0.6088 0.0567
-4.250 0.3459 0.02794 0.01958 -0.1691 0.5972 0.0584
-4.000 0.3755 0.02650 0.01772 -0.1707 0.5873 0.0604
-3.750 0.4027 0.02580 0.01685 -0.1711 0.5776 0.0626
-3.500 0.4323 0.02470 0.01529 -0.1720 0.5699 0.0652
-3.250 0.4600 0.02385 0.01420 -0.1724 0.5618 0.0672
-3.000 0.4873 0.02343 0.01365 -0.1724 0.5544 0.0698
-2.750 0.5159 0.02290 0.01279 -0.1726 0.5480 0.0738
-2.500 0.5424 0.02255 0.01244 -0.1725 0.5410 0.0769
-2.250 0.5699 0.02220 0.01191 -0.1724 0.5350 0.0810
-2.000 0.5980 0.02197 0.01154 -0.1724 0.5301 0.0860
-1.750 0.6251 0.02173 0.01120 -0.1722 0.5247 0.0924
-1.500 0.6521 0.02158 0.01105 -0.1721 0.5198 0.0996
-1.250 0.6797 0.02145 0.01086 -0.1720 0.5153 0.1090
-0.750 0.7349 0.02134 0.01066 -0.1719 0.5066 0.1380
-0.500 0.7618 0.02135 0.01065 -0.1717 0.5020 0.1582
-0.250 0.7888 0.02141 0.01069 -0.1715 0.4980 0.1801
0.000 0.8163 0.02152 0.01077 -0.1714 0.4946 0.2027
0.250 0.8443 0.02169 0.01086 -0.1713 0.4916 0.2266
0.500 0.8699 0.02186 0.01107 -0.1709 0.4878 0.2505
0.750 0.8961 0.02203 0.01125 -0.1706 0.4839 0.2740
1.000 0.9231 0.02220 0.01140 -0.1704 0.4802 0.2967
1.250 0.9509 0.02238 0.01156 -0.1703 0.4769 0.3194
1.500 0.9797 0.02259 0.01171 -0.1705 0.4741 0.3435
1.750 1.0072 0.02284 0.01197 -0.1704 0.4712 0.3689
2.000 1.0328 0.02310 0.01229 -0.1700 0.4677 0.3963
2.250 1.0589 0.02335 0.01260 -0.1698 0.4642 0.4256
2.500 1.0855 0.02360 0.01288 -0.1695 0.4610 0.4592
2.750 1.1127 0.02384 0.01314 -0.1694 0.4581 0.4969
3.000 1.1406 0.02409 0.01339 -0.1693 0.4555 0.5390
3.250 1.1668 0.02439 0.01375 -0.1691 0.4528 0.5841
3.500 1.1896 0.02471 0.01423 -0.1683 0.4494 0.6326
3.750 1.2136 0.02497 0.01463 -0.1677 0.4461 0.6900
4.000 1.2416 0.02491 0.01485 -0.1678 0.4430 0.9943
4.250 1.2635 0.02531 0.01513 -0.1668 0.4402 1.0000
4.500 1.2906 0.02571 0.01540 -0.1667 0.4376 1.0000
4.750 1.3191 0.02614 0.01567 -0.1669 0.4353 1.0000
5.000 1.3380 0.02675 0.01636 -0.1656 0.4322 1.0000
5.250 1.3582 0.02735 0.01699 -0.1646 0.4291 1.0000
5.500 1.3796 0.02789 0.01754 -0.1637 0.4259 1.0000
5.750 1.4027 0.02838 0.01800 -0.1631 0.4230 1.0000
6.000 1.4275 0.02883 0.01838 -0.1627 0.4205 1.0000
6.250 1.4542 0.02926 0.01873 -0.1626 0.4182 1.0000
6.500 1.4769 0.02986 0.01932 -0.1620 0.4159 1.0000
6.750 1.4900 0.03071 0.02031 -0.1600 0.4128 1.0000
7.000 1.5049 0.03148 0.02118 -0.1583 0.4097 1.0000
7.250 1.5223 0.03216 0.02190 -0.1569 0.4067 1.0000
7.500 1.5427 0.03272 0.02246 -0.1560 0.4040 1.0000
7.750 1.5665 0.03318 0.02289 -0.1555 0.4016 1.0000
8.000 1.5936 0.03360 0.02326 -0.1555 0.3995 1.0000
8.250 1.6034 0.03461 0.02439 -0.1532 0.3968 1.0000
8.500 1.6037 0.03588 0.02584 -0.1496 0.3936 1.0000
8.750 1.6072 0.03702 0.02710 -0.1465 0.3906 1.0000
9.000 1.6158 0.03800 0.02815 -0.1441 0.3879 1.0000
9.250 1.6315 0.03872 0.02891 -0.1427 0.3854 1.0000
9.500 1.6550 0.03916 0.02934 -0.1423 0.3832 1.0000
9.750 1.6859 0.03941 0.02953 -0.1428 0.3813 1.0000
10.000 1.6475 0.04250 0.03294 -0.1355 0.3772 1.0000
10.250 1.6199 0.04573 0.03641 -0.1306 0.3730 1.0000
10.500 1.6135 0.04801 0.03882 -0.1279 0.3698 1.0000
10.750 1.6235 0.04930 0.04016 -0.1265 0.3675 1.0000
11.000 1.6480 0.04960 0.04046 -0.1262 0.3657 1.0000
11.250 1.6824 0.04930 0.04012 -0.1265 0.3642 1.0000
11.500 1.4773 0.07082 0.06226 -0.1186 0.3488 1.0000
11.750 1.5059 0.07028 0.06173 -0.1179 0.3479 1.0000
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Polar data table (+)
Polar graphs
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