NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 50,000 Max Cl/Cd: 34.26 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2411-il-50000.txt Download as CSV file: xf-naca2411-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2.5411
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4047 0.10684 0.09945 -0.0207 1.0000 0.2867
-8.750 -0.3821 0.10192 0.09450 -0.0195 1.0000 0.2956
-8.500 -0.4035 0.10086 0.09361 -0.0193 1.0000 0.3045
-8.250 -0.3853 0.09684 0.08957 -0.0180 1.0000 0.3164
-8.000 -0.3799 0.09363 0.08641 -0.0169 1.0000 0.3269
-7.750 -0.3840 0.09121 0.08408 -0.0155 1.0000 0.3403
-7.500 -0.4088 0.09063 0.08368 -0.0135 1.0000 0.3520
-7.250 -0.4048 0.08778 0.08089 -0.0114 1.0000 0.3681
-7.000 -0.3868 0.08383 0.07693 -0.0100 1.0000 0.3814
-6.750 -0.3848 0.08093 0.07409 -0.0080 1.0000 0.3936
-6.500 -0.5108 0.06464 0.05786 -0.0306 1.0000 0.1857
-6.250 -0.5343 0.05500 0.04752 -0.0348 1.0000 0.1618
-6.000 -0.5300 0.05087 0.04301 -0.0340 1.0000 0.1604
-5.750 -0.5229 0.04701 0.03877 -0.0330 1.0000 0.1605
-5.500 -0.5130 0.04333 0.03459 -0.0320 1.0000 0.1609
-5.250 -0.4978 0.04111 0.03250 -0.0304 1.0000 0.1656
-5.000 -0.4834 0.03862 0.02965 -0.0292 1.0000 0.1715
-4.750 -0.4674 0.03575 0.02603 -0.0282 1.0000 0.1763
-4.500 -0.4497 0.03415 0.02455 -0.0268 1.0000 0.1854
-4.250 -0.4310 0.03218 0.02220 -0.0257 1.0000 0.1950
-4.000 -0.4114 0.03071 0.02040 -0.0245 1.0000 0.2082
-3.750 -0.3913 0.02943 0.01896 -0.0234 1.0000 0.2228
-3.500 -0.3713 0.02829 0.01778 -0.0222 1.0000 0.2407
-3.250 -0.3514 0.02727 0.01682 -0.0210 1.0000 0.2612
-3.000 -0.3312 0.02638 0.01582 -0.0199 1.0000 0.2878
-2.750 -0.3107 0.02553 0.01504 -0.0188 1.0000 0.3203
-2.500 -0.2914 0.02471 0.01445 -0.0174 1.0000 0.3589
-2.250 -0.2708 0.02395 0.01390 -0.0163 1.0000 0.4128
-2.000 -0.2512 0.02318 0.01356 -0.0149 1.0000 0.4860
-1.750 -0.2354 0.02229 0.01342 -0.0122 1.0000 0.5996
-1.500 -0.1595 0.02120 0.01318 -0.0195 1.0000 1.0000
-1.250 -0.1448 0.02149 0.01305 -0.0187 1.0000 1.0000
-1.000 -0.1300 0.02185 0.01311 -0.0178 1.0000 1.0000
-0.750 -0.1151 0.02229 0.01329 -0.0169 1.0000 1.0000
-0.500 -0.1000 0.02278 0.01356 -0.0161 1.0000 1.0000
-0.250 -0.0849 0.02333 0.01390 -0.0154 1.0000 1.0000
0.000 -0.0698 0.02393 0.01433 -0.0148 1.0000 1.0000
0.250 -0.0219 0.02520 0.01538 -0.0203 0.9868 1.0000
0.500 0.0286 0.02648 0.01647 -0.0260 0.9718 1.0000
0.750 0.0760 0.02760 0.01744 -0.0310 0.9565 1.0000
1.000 0.1181 0.02855 0.01827 -0.0349 0.9411 1.0000
1.250 0.1592 0.02944 0.01907 -0.0384 0.9257 1.0000
1.500 0.1994 0.03029 0.01985 -0.0416 0.9106 1.0000
1.750 0.2390 0.03108 0.02060 -0.0445 0.8957 1.0000
2.000 0.2744 0.03180 0.02129 -0.0467 0.8805 1.0000
2.250 0.3080 0.03251 0.02199 -0.0484 0.8654 1.0000
2.500 0.3406 0.03320 0.02268 -0.0498 0.8502 1.0000
2.750 0.3722 0.03389 0.02338 -0.0510 0.8352 1.0000
3.000 0.4031 0.03457 0.02409 -0.0520 0.8201 1.0000
3.250 0.4340 0.03524 0.02480 -0.0529 0.8050 1.0000
3.500 0.4646 0.03588 0.02549 -0.0536 0.7898 1.0000
3.750 0.4951 0.03650 0.02619 -0.0542 0.7746 1.0000
4.000 0.5262 0.03707 0.02683 -0.0547 0.7592 1.0000
4.250 0.5579 0.03756 0.02743 -0.0551 0.7436 1.0000
4.500 0.5910 0.03794 0.02792 -0.0555 0.7277 1.0000
4.750 0.6270 0.03809 0.02821 -0.0560 0.7116 1.0000
5.000 0.6680 0.03792 0.02821 -0.0568 0.6953 1.0000
5.250 0.7118 0.03742 0.02789 -0.0574 0.6785 1.0000
5.500 0.7609 0.03637 0.02707 -0.0579 0.6611 1.0000
5.750 0.7982 0.03578 0.02664 -0.0572 0.6413 1.0000
6.000 0.8284 0.03540 0.02641 -0.0556 0.6189 1.0000
6.250 0.8849 0.03323 0.02442 -0.0557 0.5944 1.0000
6.500 0.9256 0.03184 0.02311 -0.0544 0.5656 1.0000
6.750 0.9600 0.03078 0.02207 -0.0524 0.5331 1.0000
7.000 0.9805 0.03048 0.02179 -0.0493 0.4978 1.0000
7.250 1.0033 0.02997 0.02118 -0.0463 0.4573 1.0000
7.500 1.0184 0.02989 0.02096 -0.0425 0.4126 1.0000
7.750 1.0304 0.03008 0.02087 -0.0385 0.3635 1.0000
8.000 1.0394 0.03085 0.02121 -0.0345 0.3144 1.0000
8.250 1.0478 0.03226 0.02229 -0.0309 0.2714 1.0000
8.500 1.0599 0.03403 0.02377 -0.0283 0.2364 1.0000
8.750 1.0775 0.03599 0.02545 -0.0266 0.2088 1.0000
9.000 1.0926 0.03815 0.02771 -0.0246 0.1884 1.0000
9.250 1.1113 0.04047 0.03005 -0.0233 0.1720 1.0000
9.500 1.1289 0.04296 0.03263 -0.0219 0.1594 1.0000
9.750 1.1486 0.04571 0.03540 -0.0210 0.1493 1.0000
10.000 1.1580 0.04835 0.03838 -0.0187 0.1418 1.0000
10.250 1.1722 0.05151 0.04168 -0.0174 0.1355 1.0000
10.500 1.1689 0.05483 0.04549 -0.0141 0.1327 1.0000
10.750 1.1648 0.05815 0.04917 -0.0111 0.1297 1.0000
11.000 1.1885 0.06140 0.05230 -0.0111 0.1238 1.0000
11.250 1.1757 0.06516 0.05641 -0.0078 0.1227 1.0000
11.500 1.1566 0.06887 0.06045 -0.0044 0.1224 1.0000
11.750 1.1350 0.07268 0.06450 -0.0011 0.1225 1.0000
12.000 1.1129 0.07696 0.06898 0.0011 0.1228 1.0000
12.250 1.0907 0.08179 0.07397 0.0022 0.1232 1.0000
12.500 0.9450 0.09895 0.09151 -0.0071 0.1388 1.0000
12.750 0.9437 0.10439 0.09697 -0.0081 0.1373 1.0000
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Polar data table (+)
Polar graphs
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