NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 200,000 Max Cl/Cd: 75.37 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca642415-il-200000.txt Download as CSV file: xf-naca642415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-415
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4581 0.11273 0.10896 -0.0500 1.0000 0.0712
-12.250 -0.4325 0.11271 0.10891 -0.0461 1.0000 0.0729
-12.000 -0.4222 0.11051 0.10671 -0.0457 1.0000 0.0749
-11.750 -0.4207 0.10689 0.10312 -0.0471 1.0000 0.0774
-11.500 -0.4758 0.09354 0.08988 -0.0610 1.0000 0.0822
-11.250 -0.5214 0.08478 0.08110 -0.0686 1.0000 0.0823
-11.000 -0.4783 0.08430 0.08071 -0.0622 1.0000 0.0848
-10.750 -0.4629 0.08373 0.08017 -0.0597 1.0000 0.0862
-10.500 -0.4729 0.07837 0.07485 -0.0624 1.0000 0.0879
-10.250 -0.5099 0.07062 0.06712 -0.0677 1.0000 0.0887
-10.000 -0.6809 0.07199 0.06811 -0.0610 0.9954 0.0826
-9.750 -0.7162 0.04736 0.04232 -0.0660 0.9855 0.0497
-9.500 -0.6976 0.04222 0.03687 -0.0686 0.9791 0.0484
-9.250 -0.6756 0.03769 0.03189 -0.0710 0.9727 0.0476
-9.000 -0.6494 0.03421 0.02797 -0.0731 0.9670 0.0477
-8.750 -0.6201 0.03178 0.02512 -0.0749 0.9606 0.0490
-8.500 -0.5841 0.02944 0.02237 -0.0775 0.9572 0.0498
-8.250 -0.5524 0.02759 0.02021 -0.0790 0.9513 0.0505
-8.000 -0.5196 0.02506 0.01762 -0.0806 0.9461 0.0520
-7.750 -0.4830 0.02381 0.01634 -0.0828 0.9418 0.0545
-7.500 -0.4525 0.02276 0.01519 -0.0835 0.9346 0.0569
-7.250 -0.4207 0.02172 0.01401 -0.0843 0.9278 0.0588
-7.000 -0.3906 0.02036 0.01263 -0.0849 0.9217 0.0613
-6.750 -0.3666 0.01956 0.01188 -0.0845 0.9124 0.0647
-6.500 -0.3401 0.01889 0.01115 -0.0844 0.9050 0.0684
-6.250 -0.3187 0.01808 0.01031 -0.0834 0.8954 0.0720
-6.000 -0.2968 0.01736 0.00963 -0.0826 0.8872 0.0774
-5.750 -0.2750 0.01675 0.00897 -0.0818 0.8783 0.0843
-5.500 -0.2532 0.01610 0.00833 -0.0810 0.8703 0.0947
-5.250 -0.2325 0.01527 0.00761 -0.0803 0.8617 0.1152
-5.000 -0.2154 0.01373 0.00672 -0.0797 0.8538 0.2292
-4.750 -0.1986 0.01242 0.00649 -0.0789 0.8452 0.4773
-4.500 -0.1719 0.01247 0.00656 -0.0783 0.8388 0.5293
-4.250 -0.1457 0.01260 0.00663 -0.0778 0.8306 0.5582
-4.000 -0.1181 0.01273 0.00670 -0.0773 0.8248 0.5789
-3.750 -0.0920 0.01290 0.00684 -0.0767 0.8170 0.5961
-3.500 -0.0648 0.01305 0.00693 -0.0762 0.8105 0.6121
-3.250 -0.0382 0.01326 0.00710 -0.0755 0.8041 0.6278
-3.000 -0.0123 0.01349 0.00732 -0.0747 0.7966 0.6433
-2.750 0.0142 0.01379 0.00759 -0.0736 0.7912 0.6599
-2.500 0.0397 0.01404 0.00782 -0.0728 0.7836 0.6733
-2.250 0.0666 0.01406 0.00782 -0.0723 0.7776 0.6790
-2.000 0.0948 0.01404 0.00772 -0.0723 0.7723 0.6846
-1.750 0.1230 0.01399 0.00759 -0.0727 0.7651 0.6912
-1.500 0.1505 0.01396 0.00753 -0.0725 0.7599 0.6954
-1.250 0.1781 0.01398 0.00752 -0.0724 0.7541 0.7007
-1.000 0.2067 0.01395 0.00740 -0.0729 0.7475 0.7074
-0.750 0.2349 0.01390 0.00731 -0.0728 0.7426 0.7113
-0.500 0.2621 0.01394 0.00736 -0.0728 0.7369 0.7160
-0.250 0.2903 0.01395 0.00734 -0.0731 0.7311 0.7222
0.000 0.3193 0.01393 0.00726 -0.0734 0.7266 0.7271
0.250 0.3466 0.01399 0.00734 -0.0733 0.7218 0.7317
0.500 0.3741 0.01405 0.00741 -0.0735 0.7160 0.7378
0.750 0.4028 0.01405 0.00739 -0.0737 0.7113 0.7438
1.000 0.4308 0.01412 0.00745 -0.0737 0.7074 0.7490
1.250 0.4577 0.01424 0.00763 -0.0738 0.7017 0.7558
1.500 0.4852 0.01431 0.00772 -0.0739 0.6971 0.7615
1.750 0.5134 0.01436 0.00778 -0.0739 0.6933 0.7675
2.000 0.5415 0.01451 0.00795 -0.0742 0.6886 0.7752
2.250 0.5664 0.01463 0.00818 -0.0737 0.6834 0.7809
2.500 0.5946 0.01469 0.00825 -0.0738 0.6789 0.7889
2.750 0.6229 0.01476 0.00832 -0.0738 0.6751 0.7956
3.000 0.6470 0.01494 0.00864 -0.0733 0.6689 0.8032
3.250 0.6741 0.01503 0.00878 -0.0732 0.6642 0.8109
3.500 0.7017 0.01510 0.00888 -0.0730 0.6604 0.8185
3.750 0.7268 0.01528 0.00917 -0.0727 0.6552 0.8270
4.000 0.7512 0.01537 0.00936 -0.0720 0.6492 0.8356
4.250 0.7797 0.01526 0.00922 -0.0717 0.6433 0.8442
4.500 0.8020 0.01526 0.00937 -0.0706 0.6339 0.8542
4.750 0.8277 0.01502 0.00911 -0.0696 0.6249 0.8629
5.000 0.8516 0.01484 0.00899 -0.0686 0.6137 0.8734
5.250 0.8726 0.01471 0.00896 -0.0669 0.6032 0.8838
5.500 0.8946 0.01446 0.00872 -0.0652 0.5910 0.8949
5.750 0.9160 0.01421 0.00847 -0.0635 0.5779 0.9076
6.000 0.9334 0.01405 0.00843 -0.0612 0.5647 0.9222
6.250 0.9511 0.01389 0.00837 -0.0590 0.5514 0.9389
6.500 0.9722 0.01373 0.00828 -0.0575 0.5359 0.9590
6.750 1.0052 0.01362 0.00821 -0.0586 0.5141 0.9812
7.000 1.0325 0.01370 0.00832 -0.0591 0.4840 1.0000
7.250 1.0534 0.01398 0.00851 -0.0585 0.4358 1.0000
7.500 1.0593 0.01503 0.00899 -0.0557 0.3366 1.0000
7.750 1.0534 0.01686 0.01018 -0.0516 0.2408 1.0000
8.000 1.0449 0.01868 0.01151 -0.0471 0.1703 1.0000
8.250 1.0395 0.02055 0.01300 -0.0435 0.1212 1.0000
8.500 1.0387 0.02230 0.01454 -0.0407 0.0958 1.0000
8.750 1.0419 0.02391 0.01606 -0.0385 0.0821 1.0000
9.000 1.0461 0.02553 0.01764 -0.0365 0.0738 1.0000
9.250 1.0515 0.02714 0.01921 -0.0349 0.0675 1.0000
9.500 1.0593 0.02867 0.02078 -0.0334 0.0625 1.0000
9.750 1.0680 0.03017 0.02228 -0.0322 0.0584 1.0000
10.000 1.0741 0.03200 0.02407 -0.0307 0.0553 1.0000
10.250 1.0867 0.03332 0.02548 -0.0298 0.0523 1.0000
10.500 1.0982 0.03476 0.02690 -0.0288 0.0495 1.0000
10.750 1.1114 0.03637 0.02845 -0.0277 0.0468 1.0000
11.000 1.1271 0.03764 0.02983 -0.0270 0.0449 1.0000
11.250 1.1439 0.03894 0.03118 -0.0262 0.0430 1.0000
11.500 1.1625 0.04024 0.03247 -0.0256 0.0414 1.0000
11.750 1.1971 0.04169 0.03384 -0.0256 0.0396 1.0000
12.000 1.2111 0.04323 0.03558 -0.0248 0.0386 1.0000
12.250 1.2268 0.04488 0.03741 -0.0241 0.0375 1.0000
12.500 1.2415 0.04659 0.03924 -0.0235 0.0362 1.0000
12.750 1.2588 0.04841 0.04119 -0.0230 0.0355 1.0000
13.000 1.2737 0.05044 0.04335 -0.0225 0.0347 1.0000
13.250 1.2900 0.05268 0.04569 -0.0221 0.0342 1.0000
13.500 1.3094 0.05557 0.04871 -0.0220 0.0336 1.0000
13.750 1.3210 0.05940 0.05278 -0.0216 0.0333 1.0000
14.000 1.3199 0.06324 0.05687 -0.0208 0.0332 1.0000
14.250 1.3122 0.06685 0.06074 -0.0199 0.0332 1.0000
14.500 1.3009 0.07075 0.06490 -0.0193 0.0331 1.0000
14.750 1.2880 0.07498 0.06938 -0.0190 0.0331 1.0000
15.000 1.2725 0.07956 0.07421 -0.0192 0.0331 1.0000
15.250 1.2553 0.08455 0.07943 -0.0198 0.0331 1.0000
15.500 1.2397 0.08999 0.08509 -0.0209 0.0332 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(2)-415 (naca642415-il)