NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-415 AIRFOIL (n63415-il) Reynolds number: 200,000 Max Cl/Cd: 75.56 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63415-il-200000.txt Download as CSV file: xf-n63415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-415 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5572 0.08098 0.07718 -0.0622 1.0000 0.0521
-12.000 -0.5431 0.08015 0.07639 -0.0614 1.0000 0.0531
-11.750 -0.7186 0.05732 0.05267 -0.0761 1.0000 0.0426
-11.500 -0.7310 0.05354 0.04881 -0.0753 1.0000 0.0423
-11.250 -0.7486 0.05077 0.04594 -0.0729 1.0000 0.0421
-11.000 -0.7650 0.04822 0.04326 -0.0699 1.0000 0.0420
-10.750 -0.7820 0.04612 0.04103 -0.0660 1.0000 0.0419
-10.500 -0.8038 0.04483 0.03964 -0.0603 1.0000 0.0418
-10.250 -0.8175 0.04309 0.03768 -0.0565 0.9987 0.0420
-10.000 -0.7954 0.03961 0.03356 -0.0600 0.9910 0.0429
-9.750 -0.7690 0.03547 0.02927 -0.0628 0.9858 0.0442
-9.500 -0.7355 0.03320 0.02684 -0.0656 0.9815 0.0453
-9.250 -0.7048 0.03110 0.02452 -0.0675 0.9749 0.0467
-9.000 -0.6691 0.02909 0.02221 -0.0703 0.9708 0.0487
-8.750 -0.6364 0.02789 0.02064 -0.0721 0.9643 0.0506
-8.500 -0.6015 0.02539 0.01816 -0.0743 0.9603 0.0529
-8.250 -0.5626 0.02406 0.01675 -0.0770 0.9568 0.0555
-8.000 -0.5280 0.02307 0.01561 -0.0787 0.9510 0.0588
-7.750 -0.4958 0.02161 0.01413 -0.0800 0.9446 0.0618
-7.500 -0.4599 0.02055 0.01309 -0.0820 0.9399 0.0656
-7.250 -0.4328 0.01991 0.01236 -0.0822 0.9307 0.0696
-7.000 -0.4037 0.01875 0.01126 -0.0829 0.9242 0.0743
-6.750 -0.3805 0.01814 0.01063 -0.0824 0.9143 0.0793
-6.500 -0.3550 0.01730 0.00978 -0.0824 0.9071 0.0858
-6.250 -0.3338 0.01675 0.00922 -0.0815 0.8969 0.0937
-6.000 -0.3100 0.01597 0.00846 -0.0812 0.8899 0.1080
-5.750 -0.2910 0.01506 0.00776 -0.0804 0.8797 0.1405
-5.500 -0.2724 0.01345 0.00689 -0.0803 0.8724 0.2746
-5.250 -0.2515 0.01269 0.00669 -0.0798 0.8631 0.4083
-5.000 -0.2245 0.01256 0.00663 -0.0794 0.8570 0.4637
-4.750 -0.1987 0.01259 0.00667 -0.0790 0.8483 0.4962
-4.500 -0.1709 0.01262 0.00661 -0.0787 0.8419 0.5225
-4.250 -0.1443 0.01271 0.00668 -0.0782 0.8343 0.5420
-4.000 -0.1172 0.01280 0.00673 -0.0778 0.8273 0.5602
-3.750 -0.0900 0.01296 0.00685 -0.0772 0.8211 0.5787
-3.500 -0.0637 0.01314 0.00703 -0.0766 0.8131 0.5959
-3.250 -0.0361 0.01326 0.00708 -0.0761 0.8074 0.6102
-3.000 -0.0089 0.01337 0.00713 -0.0759 0.7999 0.6230
-2.750 0.0176 0.01347 0.00724 -0.0751 0.7933 0.6331
-2.500 0.0451 0.01356 0.00729 -0.0747 0.7874 0.6441
-2.250 0.0722 0.01361 0.00731 -0.0745 0.7799 0.6532
-2.000 0.1004 0.01359 0.00721 -0.0743 0.7743 0.6604
-1.750 0.1275 0.01364 0.00725 -0.0741 0.7672 0.6679
-1.500 0.1556 0.01361 0.00716 -0.0741 0.7607 0.6757
-1.250 0.1838 0.01364 0.00713 -0.0739 0.7559 0.6822
-1.000 0.2116 0.01366 0.00712 -0.0741 0.7481 0.6907
-0.750 0.2388 0.01365 0.00712 -0.0737 0.7423 0.6963
-0.500 0.2670 0.01369 0.00712 -0.0738 0.7364 0.7038
-0.250 0.2944 0.01370 0.00713 -0.0737 0.7296 0.7105
0.000 0.3226 0.01370 0.00710 -0.0736 0.7244 0.7169
0.250 0.3508 0.01374 0.00713 -0.0739 0.7177 0.7249
0.500 0.3775 0.01377 0.00720 -0.0735 0.7116 0.7307
0.750 0.4070 0.01379 0.00714 -0.0737 0.7069 0.7385
1.000 0.4330 0.01386 0.00728 -0.0734 0.6996 0.7448
1.250 0.4607 0.01389 0.00732 -0.0733 0.6938 0.7521
1.500 0.4895 0.01393 0.00733 -0.0734 0.6889 0.7597
1.750 0.5150 0.01401 0.00750 -0.0730 0.6816 0.7662
2.000 0.5441 0.01404 0.00749 -0.0732 0.6762 0.7747
2.250 0.5698 0.01412 0.00765 -0.0727 0.6701 0.7812
2.500 0.5975 0.01420 0.00775 -0.0728 0.6633 0.7900
2.750 0.6245 0.01421 0.00777 -0.0723 0.6582 0.7964
3.000 0.6507 0.01434 0.00799 -0.0721 0.6510 0.8053
3.250 0.6766 0.01438 0.00807 -0.0716 0.6448 0.8126
3.500 0.7045 0.01446 0.00816 -0.0715 0.6392 0.8216
3.750 0.7284 0.01453 0.00835 -0.0707 0.6315 0.8293
4.000 0.7571 0.01455 0.00834 -0.0707 0.6256 0.8390
4.250 0.7792 0.01460 0.00852 -0.0695 0.6169 0.8471
4.500 0.8071 0.01452 0.00841 -0.0692 0.6091 0.8568
4.750 0.8284 0.01452 0.00854 -0.0678 0.5990 0.8663
5.000 0.8537 0.01447 0.00848 -0.0669 0.5910 0.8760
5.250 0.8766 0.01443 0.00855 -0.0659 0.5804 0.8874
5.500 0.8972 0.01436 0.00855 -0.0642 0.5703 0.8985
5.750 0.9187 0.01422 0.00840 -0.0625 0.5593 0.9108
6.000 0.9373 0.01403 0.00826 -0.0604 0.5446 0.9253
6.250 0.9556 0.01385 0.00813 -0.0583 0.5287 0.9428
6.500 0.9786 0.01372 0.00807 -0.0573 0.5128 0.9632
6.750 1.0134 0.01372 0.00815 -0.0590 0.4938 1.0000
7.000 1.0412 0.01388 0.00836 -0.0597 0.4727 1.0000
7.250 1.0677 0.01413 0.00855 -0.0600 0.4482 1.0000
7.500 1.0916 0.01448 0.00886 -0.0599 0.4158 1.0000
7.750 1.1107 0.01505 0.00927 -0.0591 0.3699 1.0000
8.000 1.1218 0.01604 0.00992 -0.0572 0.3083 1.0000
8.250 1.1252 0.01744 0.01091 -0.0543 0.2429 1.0000
8.500 1.1222 0.01900 0.01209 -0.0505 0.1869 1.0000
8.750 1.1177 0.02076 0.01350 -0.0469 0.1417 1.0000
9.000 1.1151 0.02258 0.01509 -0.0439 0.1110 1.0000
9.250 1.1159 0.02431 0.01671 -0.0415 0.0933 1.0000
9.500 1.1187 0.02603 0.01837 -0.0395 0.0831 1.0000
9.750 1.1210 0.02787 0.02014 -0.0377 0.0761 1.0000
10.000 1.1294 0.02936 0.02168 -0.0364 0.0702 1.0000
10.250 1.1339 0.03118 0.02347 -0.0351 0.0658 1.0000
10.500 1.1414 0.03287 0.02522 -0.0339 0.0621 1.0000
10.750 1.1505 0.03445 0.02684 -0.0330 0.0585 1.0000
11.000 1.1570 0.03634 0.02867 -0.0319 0.0556 1.0000
11.250 1.1675 0.03797 0.03037 -0.0309 0.0529 1.0000
11.500 1.1786 0.03951 0.03198 -0.0302 0.0502 1.0000
11.750 1.1891 0.04118 0.03362 -0.0295 0.0478 1.0000
12.000 1.2052 0.04276 0.03519 -0.0285 0.0457 1.0000
12.250 1.2188 0.04431 0.03686 -0.0278 0.0439 1.0000
12.500 1.2324 0.04591 0.03854 -0.0272 0.0422 1.0000
12.750 1.2466 0.04748 0.04011 -0.0267 0.0405 1.0000
13.000 1.2701 0.04914 0.04175 -0.0261 0.0386 1.0000
13.250 1.2783 0.05117 0.04399 -0.0255 0.0376 1.0000
13.500 1.2895 0.05328 0.04629 -0.0249 0.0366 1.0000
13.750 1.3004 0.05549 0.04865 -0.0245 0.0358 1.0000
14.000 1.3105 0.05777 0.05107 -0.0241 0.0350 1.0000
14.250 1.3182 0.06028 0.05372 -0.0237 0.0343 1.0000
14.500 1.3262 0.06287 0.05645 -0.0235 0.0338 1.0000
14.750 1.3377 0.06567 0.05932 -0.0233 0.0331 1.0000
15.000 1.3433 0.06992 0.06376 -0.0232 0.0326 1.0000
15.250 1.3305 0.07394 0.06805 -0.0234 0.0324 1.0000
15.500 1.3155 0.07842 0.07281 -0.0240 0.0323 1.0000
15.750 1.3003 0.08331 0.07796 -0.0251 0.0322 1.0000
16.000 1.2827 0.08875 0.08367 -0.0267 0.0321 1.0000
16.250 1.2641 0.09470 0.08987 -0.0289 0.0320 1.0000
16.500 1.2443 0.10123 0.09664 -0.0317 0.0320 1.0000
16.750 1.2233 0.10832 0.10396 -0.0352 0.0321 1.0000
17.000 1.2010 0.11606 0.11191 -0.0394 0.0322 1.0000
17.250 1.1787 0.12433 0.12039 -0.0443 0.0323 1.0000
17.500 1.1564 0.13314 0.12937 -0.0497 0.0325 1.0000
17.750 1.1317 0.14302 0.13946 -0.0565 0.0328 1.0000
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Polar data table (+)
Polar graphs
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