NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 500,000 Max Cl/Cd: 86.64 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2411-il-500000-n5.txt Download as CSV file: xf-naca2411-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7887 0.08815 0.08512 -0.0451 1.0000 0.0144
-14.750 -0.8344 0.07638 0.07323 -0.0521 1.0000 0.0143
-14.500 -0.8770 0.06533 0.06204 -0.0590 1.0000 0.0142
-14.250 -0.9090 0.05565 0.05221 -0.0658 1.0000 0.0142
-14.000 -0.9352 0.04648 0.04283 -0.0735 1.0000 0.0141
-13.750 -0.9555 0.03978 0.03592 -0.0792 1.0000 0.0141
-13.500 -0.9671 0.03622 0.03220 -0.0806 1.0000 0.0142
-13.250 -0.9793 0.03375 0.02957 -0.0792 1.0000 0.0143
-13.000 -0.9909 0.03212 0.02781 -0.0756 1.0000 0.0143
-12.750 -0.9983 0.03077 0.02632 -0.0715 1.0000 0.0144
-12.500 -0.9992 0.02939 0.02481 -0.0683 1.0000 0.0146
-12.250 -0.9999 0.02799 0.02330 -0.0650 1.0000 0.0147
-12.000 -0.9967 0.02680 0.02202 -0.0619 1.0000 0.0149
-11.750 -0.9902 0.02579 0.02093 -0.0591 1.0000 0.0151
-11.500 -0.9796 0.02485 0.01989 -0.0570 0.9998 0.0153
-11.250 -0.9536 0.02378 0.01871 -0.0578 0.9979 0.0156
-11.000 -0.9270 0.02279 0.01760 -0.0587 0.9957 0.0160
-10.750 -0.9000 0.02185 0.01654 -0.0595 0.9936 0.0163
-10.500 -0.8745 0.02098 0.01556 -0.0599 0.9910 0.0167
-10.250 -0.8474 0.02017 0.01462 -0.0604 0.9883 0.0172
-10.000 -0.8189 0.01941 0.01373 -0.0612 0.9861 0.0176
-9.750 -0.7899 0.01855 0.01277 -0.0621 0.9842 0.0181
-9.500 -0.7639 0.01776 0.01191 -0.0624 0.9813 0.0186
-9.250 -0.7373 0.01712 0.01121 -0.0626 0.9778 0.0191
-9.000 -0.7081 0.01654 0.01056 -0.0632 0.9752 0.0197
-8.750 -0.6776 0.01595 0.00990 -0.0641 0.9731 0.0202
-8.500 -0.6459 0.01540 0.00926 -0.0653 0.9715 0.0209
-8.250 -0.6191 0.01494 0.00873 -0.0652 0.9676 0.0217
-8.000 -0.5917 0.01436 0.00811 -0.0654 0.9638 0.0226
-7.750 -0.5609 0.01388 0.00760 -0.0662 0.9611 0.0237
-7.500 -0.5283 0.01344 0.00711 -0.0674 0.9589 0.0248
-7.250 -0.4951 0.01302 0.00662 -0.0687 0.9569 0.0260
-7.000 -0.4707 0.01261 0.00619 -0.0680 0.9504 0.0274
-6.750 -0.4403 0.01222 0.00578 -0.0686 0.9461 0.0293
-6.500 -0.4066 0.01187 0.00537 -0.0699 0.9425 0.0314
-6.250 -0.3805 0.01152 0.00503 -0.0695 0.9345 0.0341
-6.000 -0.3488 0.01122 0.00469 -0.0703 0.9288 0.0373
-5.750 -0.3206 0.01091 0.00438 -0.0704 0.9219 0.0407
-5.500 -0.2916 0.01065 0.00409 -0.0706 0.9150 0.0445
-5.250 -0.2628 0.01039 0.00382 -0.0708 0.9082 0.0490
-5.000 -0.2349 0.01017 0.00358 -0.0707 0.9000 0.0540
-4.750 -0.2070 0.00993 0.00334 -0.0707 0.8920 0.0603
-4.500 -0.1793 0.00973 0.00313 -0.0705 0.8828 0.0667
-4.250 -0.1522 0.00953 0.00293 -0.0703 0.8733 0.0752
-4.000 -0.1248 0.00933 0.00274 -0.0701 0.8636 0.0855
-3.750 -0.0983 0.00916 0.00257 -0.0697 0.8524 0.0966
-3.500 -0.0717 0.00899 0.00241 -0.0694 0.8412 0.1092
-3.250 -0.0452 0.00884 0.00226 -0.0690 0.8298 0.1235
-2.750 0.0071 0.00857 0.00202 -0.0681 0.8043 0.1587
-2.500 0.0331 0.00845 0.00191 -0.0676 0.7909 0.1783
-2.250 0.0588 0.00833 0.00182 -0.0671 0.7772 0.2009
-1.750 0.1100 0.00815 0.00167 -0.0659 0.7483 0.2493
-1.500 0.1353 0.00805 0.00161 -0.0653 0.7337 0.2779
-1.250 0.1605 0.00797 0.00157 -0.0647 0.7183 0.3096
-1.000 0.1854 0.00787 0.00153 -0.0640 0.7030 0.3456
-0.750 0.2100 0.00777 0.00149 -0.0633 0.6872 0.3860
-0.500 0.2340 0.00763 0.00148 -0.0624 0.6716 0.4402
-0.250 0.2574 0.00747 0.00148 -0.0614 0.6560 0.5098
0.000 0.2804 0.00733 0.00149 -0.0604 0.6406 0.5793
0.250 0.3032 0.00721 0.00152 -0.0592 0.6252 0.6424
0.500 0.3257 0.00709 0.00156 -0.0579 0.6102 0.7051
0.750 0.3480 0.00700 0.00161 -0.0565 0.5954 0.7665
1.000 0.3710 0.00691 0.00169 -0.0552 0.5810 0.8314
1.250 0.4001 0.00691 0.00179 -0.0551 0.5663 0.8907
1.500 0.4414 0.00703 0.00190 -0.0579 0.5504 0.9299
1.750 0.4825 0.00719 0.00200 -0.0607 0.5347 0.9512
2.000 0.5207 0.00734 0.00208 -0.0629 0.5193 0.9640
2.250 0.5563 0.00749 0.00217 -0.0645 0.5038 0.9741
2.500 0.5903 0.00766 0.00228 -0.0658 0.4888 0.9841
2.750 0.6290 0.00783 0.00238 -0.0682 0.4730 0.9926
3.000 0.6707 0.00801 0.00249 -0.0713 0.4553 0.9995
3.500 0.7160 0.00834 0.00269 -0.0691 0.4218 1.0000
3.750 0.7374 0.00852 0.00281 -0.0678 0.4024 1.0000
4.000 0.7581 0.00875 0.00294 -0.0664 0.3786 1.0000
4.250 0.7786 0.00901 0.00309 -0.0649 0.3531 1.0000
4.500 0.7990 0.00929 0.00326 -0.0634 0.3286 1.0000
4.750 0.8193 0.00958 0.00345 -0.0619 0.3028 1.0000
5.000 0.8391 0.00993 0.00367 -0.0603 0.2742 1.0000
5.250 0.8583 0.01033 0.00392 -0.0587 0.2433 1.0000
5.500 0.8772 0.01076 0.00421 -0.0570 0.2126 1.0000
5.750 0.8962 0.01119 0.00450 -0.0554 0.1849 1.0000
6.000 0.9150 0.01163 0.00482 -0.0538 0.1588 1.0000
6.250 0.9336 0.01209 0.00515 -0.0521 0.1342 1.0000
6.750 0.9707 0.01304 0.00588 -0.0488 0.0926 1.0000
7.000 0.9897 0.01348 0.00625 -0.0472 0.0781 1.0000
7.250 1.0090 0.01389 0.00662 -0.0457 0.0677 1.0000
7.500 1.0280 0.01431 0.00701 -0.0442 0.0590 1.0000
7.750 1.0469 0.01474 0.00740 -0.0426 0.0519 1.0000
8.000 1.0663 0.01513 0.00779 -0.0411 0.0468 1.0000
8.250 1.0846 0.01557 0.00822 -0.0395 0.0422 1.0000
8.500 1.1032 0.01597 0.00864 -0.0379 0.0386 1.0000
8.750 1.1205 0.01644 0.00911 -0.0362 0.0352 1.0000
9.000 1.1376 0.01686 0.00955 -0.0344 0.0325 1.0000
9.250 1.1522 0.01735 0.01004 -0.0321 0.0298 1.0000
9.500 1.1672 0.01780 0.01054 -0.0300 0.0278 1.0000
9.750 1.1816 0.01831 0.01107 -0.0278 0.0259 1.0000
10.000 1.1950 0.01889 0.01166 -0.0255 0.0243 1.0000
10.250 1.2091 0.01944 0.01226 -0.0235 0.0231 1.0000
10.500 1.2228 0.02003 0.01292 -0.0214 0.0221 1.0000
10.750 1.2357 0.02068 0.01360 -0.0193 0.0209 1.0000
11.000 1.2473 0.02142 0.01438 -0.0172 0.0201 1.0000
11.250 1.2582 0.02223 0.01524 -0.0151 0.0193 1.0000
11.500 1.2698 0.02301 0.01609 -0.0131 0.0187 1.0000
11.750 1.2809 0.02384 0.01700 -0.0112 0.0180 1.0000
12.000 1.2914 0.02475 0.01797 -0.0094 0.0174 1.0000
12.250 1.3006 0.02576 0.01904 -0.0076 0.0169 1.0000
12.500 1.3083 0.02694 0.02027 -0.0057 0.0164 1.0000
12.750 1.3135 0.02834 0.02174 -0.0039 0.0160 1.0000
13.000 1.3208 0.02965 0.02313 -0.0024 0.0157 1.0000
13.250 1.3276 0.03106 0.02464 -0.0010 0.0154 1.0000
13.500 1.3331 0.03264 0.02632 0.0003 0.0151 1.0000
13.750 1.3378 0.03438 0.02815 0.0014 0.0148 1.0000
14.000 1.3423 0.03619 0.03006 0.0023 0.0145 1.0000
14.250 1.3455 0.03822 0.03218 0.0031 0.0142 1.0000
14.500 1.3494 0.04027 0.03431 0.0036 0.0139 1.0000
14.750 1.3498 0.04275 0.03690 0.0040 0.0138 1.0000
15.000 1.3511 0.04523 0.03947 0.0042 0.0136 1.0000
15.250 1.3491 0.04821 0.04254 0.0042 0.0134 1.0000
15.500 1.3484 0.05113 0.04556 0.0039 0.0132 1.0000
15.750 1.3454 0.05443 0.04895 0.0035 0.0130 1.0000
16.000 1.3380 0.05841 0.05303 0.0027 0.0128 1.0000
16.250 1.3323 0.06229 0.05702 0.0018 0.0127 1.0000
16.500 1.3308 0.06574 0.06059 0.0008 0.0125 1.0000
16.750 1.3249 0.06986 0.06484 -0.0004 0.0124 1.0000
17.000 1.3192 0.07410 0.06919 -0.0018 0.0123 1.0000
17.250 1.3120 0.07862 0.07384 -0.0034 0.0122 1.0000
17.500 1.3046 0.08328 0.07862 -0.0051 0.0120 1.0000
17.750 1.2963 0.08820 0.08366 -0.0071 0.0119 1.0000
18.000 1.2870 0.09338 0.08896 -0.0093 0.0119 1.0000
18.250 1.2777 0.09866 0.09436 -0.0116 0.0118 1.0000
18.500 1.2682 0.10411 0.09992 -0.0140 0.0117 1.0000
18.750 1.2578 0.10986 0.10580 -0.0168 0.0116 1.0000
19.000 1.2476 0.11564 0.11169 -0.0197 0.0115 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 2.5411 (naca2411-il)