NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-415 AIRFOIL (n63415-il) Reynolds number: 500,000 Max Cl/Cd: 100.89 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63415-il-500000.txt Download as CSV file: xf-n63415-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7187 0.09149 0.08869 -0.0506 1.0000 0.0203
-15.250 -0.7729 0.07691 0.07384 -0.0605 1.0000 0.0198
-15.000 -0.8084 0.06743 0.06413 -0.0667 1.0000 0.0197
-14.750 -0.8319 0.06085 0.05736 -0.0706 1.0000 0.0197
-14.500 -0.8540 0.05497 0.05126 -0.0737 1.0000 0.0197
-14.250 -0.8685 0.05044 0.04655 -0.0757 1.0000 0.0198
-14.000 -0.8800 0.04651 0.04243 -0.0770 1.0000 0.0199
-13.750 -0.8880 0.04322 0.03896 -0.0778 1.0000 0.0202
-13.500 -0.8935 0.04030 0.03587 -0.0781 1.0000 0.0204
-13.250 -0.8968 0.03782 0.03321 -0.0780 1.0000 0.0206
-13.000 -0.8983 0.03561 0.03083 -0.0776 1.0000 0.0209
-12.750 -0.8990 0.03389 0.02892 -0.0768 1.0000 0.0211
-12.500 -0.8982 0.03149 0.02639 -0.0755 1.0000 0.0215
-12.250 -0.8916 0.03012 0.02500 -0.0742 1.0000 0.0219
-12.000 -0.8861 0.02905 0.02391 -0.0726 1.0000 0.0223
-11.750 -0.8841 0.02816 0.02299 -0.0702 1.0000 0.0226
-11.500 -0.8881 0.02742 0.02222 -0.0666 1.0000 0.0229
-11.250 -0.8784 0.02661 0.02135 -0.0652 0.9980 0.0235
-11.000 -0.8472 0.02529 0.01989 -0.0676 0.9906 0.0243
-10.750 -0.8150 0.02412 0.01855 -0.0700 0.9841 0.0251
-10.500 -0.7848 0.02250 0.01682 -0.0720 0.9774 0.0259
-10.250 -0.7513 0.02138 0.01571 -0.0744 0.9710 0.0269
-10.000 -0.7183 0.02055 0.01482 -0.0766 0.9619 0.0279
-9.750 -0.6847 0.01981 0.01400 -0.0786 0.9525 0.0293
-9.500 -0.6548 0.01923 0.01327 -0.0797 0.9401 0.0303
-9.250 -0.6348 0.01799 0.01199 -0.0793 0.9258 0.0316
-9.000 -0.6136 0.01743 0.01139 -0.0787 0.9125 0.0328
-8.750 -0.5921 0.01694 0.01082 -0.0780 0.9009 0.0341
-8.500 -0.5700 0.01651 0.01028 -0.0772 0.8906 0.0355
-8.250 -0.5504 0.01579 0.00949 -0.0763 0.8798 0.0370
-8.000 -0.5291 0.01523 0.00890 -0.0757 0.8707 0.0388
-7.750 -0.5059 0.01481 0.00843 -0.0752 0.8614 0.0406
-7.500 -0.4818 0.01445 0.00798 -0.0748 0.8534 0.0423
-7.250 -0.4598 0.01379 0.00727 -0.0742 0.8447 0.0446
-7.000 -0.4354 0.01339 0.00683 -0.0739 0.8372 0.0472
-6.750 -0.4100 0.01307 0.00645 -0.0737 0.8292 0.0498
-6.500 -0.3854 0.01260 0.00590 -0.0734 0.8223 0.0530
-6.250 -0.3596 0.01222 0.00553 -0.0734 0.8144 0.0572
-6.000 -0.3336 0.01187 0.00511 -0.0732 0.8077 0.0623
-5.750 -0.3072 0.01151 0.00475 -0.0732 0.8005 0.0702
-5.500 -0.2813 0.01100 0.00433 -0.0732 0.7934 0.0903
-5.250 -0.2557 0.01038 0.00392 -0.0734 0.7870 0.1418
-5.000 -0.2301 0.00962 0.00351 -0.0737 0.7799 0.2211
-4.750 -0.2041 0.00888 0.00313 -0.0741 0.7736 0.3201
-4.500 -0.1767 0.00844 0.00296 -0.0745 0.7668 0.3958
-4.250 -0.1483 0.00825 0.00284 -0.0747 0.7604 0.4390
-4.000 -0.1198 0.00816 0.00277 -0.0749 0.7543 0.4677
-3.750 -0.0909 0.00809 0.00271 -0.0751 0.7474 0.4880
-3.500 -0.0620 0.00806 0.00264 -0.0753 0.7414 0.5044
-3.250 -0.0331 0.00804 0.00260 -0.0755 0.7352 0.5192
-3.000 -0.0042 0.00802 0.00258 -0.0756 0.7286 0.5353
-2.750 0.0246 0.00805 0.00257 -0.0758 0.7227 0.5524
-2.500 0.0535 0.00804 0.00258 -0.0759 0.7162 0.5656
-2.250 0.0826 0.00805 0.00254 -0.0761 0.7101 0.5754
-2.000 0.1115 0.00809 0.00255 -0.0763 0.7043 0.5863
-1.750 0.1404 0.00807 0.00255 -0.0764 0.6977 0.5958
-1.500 0.1694 0.00811 0.00252 -0.0766 0.6919 0.6037
-1.250 0.1984 0.00811 0.00252 -0.0768 0.6860 0.6104
-1.000 0.2274 0.00811 0.00252 -0.0770 0.6797 0.6175
-0.750 0.2564 0.00816 0.00250 -0.0772 0.6741 0.6244
-0.500 0.2852 0.00815 0.00253 -0.0774 0.6679 0.6309
-0.250 0.3144 0.00819 0.00253 -0.0776 0.6620 0.6380
0.000 0.3431 0.00822 0.00255 -0.0778 0.6566 0.6441
0.250 0.3720 0.00823 0.00259 -0.0780 0.6503 0.6507
0.500 0.4011 0.00827 0.00260 -0.0782 0.6445 0.6573
0.750 0.4297 0.00831 0.00265 -0.0784 0.6390 0.6632
1.000 0.4587 0.00834 0.00270 -0.0786 0.6327 0.6702
1.250 0.4874 0.00838 0.00273 -0.0787 0.6270 0.6765
1.500 0.5160 0.00843 0.00280 -0.0789 0.6211 0.6828
1.750 0.5449 0.00848 0.00285 -0.0791 0.6147 0.6899
2.000 0.5732 0.00855 0.00292 -0.0792 0.6090 0.6961
2.250 0.6018 0.00859 0.00301 -0.0793 0.6027 0.7031
2.500 0.6304 0.00864 0.00308 -0.0795 0.5965 0.7097
2.750 0.6586 0.00873 0.00318 -0.0795 0.5907 0.7162
3.000 0.6873 0.00878 0.00327 -0.0797 0.5838 0.7238
3.250 0.7150 0.00886 0.00335 -0.0797 0.5768 0.7302
3.500 0.7430 0.00889 0.00345 -0.0797 0.5678 0.7375
3.750 0.7706 0.00898 0.00353 -0.0797 0.5594 0.7443
4.000 0.7983 0.00902 0.00364 -0.0796 0.5508 0.7516
4.250 0.8258 0.00912 0.00374 -0.0796 0.5416 0.7591
4.500 0.8526 0.00918 0.00385 -0.0794 0.5300 0.7661
4.750 0.8798 0.00927 0.00395 -0.0793 0.5163 0.7742
5.000 0.9057 0.00936 0.00408 -0.0789 0.5011 0.7814
5.250 0.9324 0.00950 0.00422 -0.0788 0.4867 0.7897
5.500 0.9582 0.00963 0.00439 -0.0784 0.4730 0.7971
5.750 0.9843 0.00981 0.00458 -0.0781 0.4575 0.8058
6.000 1.0089 0.01000 0.00478 -0.0776 0.4385 0.8136
6.250 1.0330 0.01029 0.00501 -0.0770 0.4132 0.8227
6.500 1.0546 0.01066 0.00531 -0.0760 0.3793 0.8311
6.750 1.0739 0.01125 0.00571 -0.0748 0.3334 0.8410
7.000 1.0892 0.01205 0.00627 -0.0730 0.2796 0.8508
7.250 1.1023 0.01297 0.00692 -0.0708 0.2239 0.8615
7.500 1.1139 0.01393 0.00763 -0.0685 0.1737 0.8737
7.750 1.1250 0.01479 0.00831 -0.0661 0.1343 0.8874
8.000 1.1333 0.01562 0.00898 -0.0630 0.1020 0.9038
8.250 1.1375 0.01628 0.00958 -0.0591 0.0796 0.9283
8.500 1.1435 0.01693 0.01019 -0.0558 0.0645 1.0000
8.750 1.1562 0.01780 0.01099 -0.0541 0.0548 1.0000
9.000 1.1708 0.01854 0.01174 -0.0527 0.0497 1.0000
9.250 1.1818 0.01948 0.01266 -0.0509 0.0456 1.0000
9.500 1.1957 0.02027 0.01349 -0.0495 0.0429 1.0000
9.750 1.2056 0.02132 0.01455 -0.0478 0.0403 1.0000
10.000 1.2147 0.02248 0.01574 -0.0461 0.0382 1.0000
10.250 1.2273 0.02345 0.01676 -0.0449 0.0363 1.0000
10.500 1.2374 0.02462 0.01797 -0.0436 0.0345 1.0000
10.750 1.2391 0.02645 0.01981 -0.0418 0.0326 1.0000
11.000 1.2523 0.02751 0.02095 -0.0409 0.0314 1.0000
11.250 1.2625 0.02882 0.02231 -0.0399 0.0298 1.0000
11.500 1.2704 0.03035 0.02388 -0.0389 0.0287 1.0000
11.750 1.2701 0.03262 0.02617 -0.0375 0.0274 1.0000
12.000 1.2778 0.03429 0.02792 -0.0367 0.0266 1.0000
12.250 1.2867 0.03591 0.02962 -0.0360 0.0257 1.0000
12.500 1.2940 0.03770 0.03147 -0.0353 0.0248 1.0000
12.750 1.3005 0.03960 0.03342 -0.0347 0.0241 1.0000
13.000 1.3047 0.04176 0.03561 -0.0342 0.0234 1.0000
13.250 1.3020 0.04464 0.03854 -0.0334 0.0226 1.0000
13.500 1.3105 0.04652 0.04051 -0.0331 0.0222 1.0000
13.750 1.3174 0.04860 0.04268 -0.0329 0.0217 1.0000
14.000 1.3239 0.05076 0.04493 -0.0327 0.0210 1.0000
14.250 1.3297 0.05305 0.04730 -0.0327 0.0205 1.0000
14.500 1.3357 0.05537 0.04968 -0.0327 0.0201 1.0000
14.750 1.3406 0.05786 0.05221 -0.0329 0.0196 1.0000
15.000 1.3446 0.06048 0.05488 -0.0330 0.0193 1.0000
15.250 1.3475 0.06325 0.05769 -0.0330 0.0189 1.0000
15.500 1.3510 0.06603 0.06056 -0.0330 0.0185 1.0000
15.750 1.3554 0.06881 0.06346 -0.0334 0.0183 1.0000
16.000 1.3588 0.07178 0.06656 -0.0340 0.0181 1.0000
16.250 1.3619 0.07485 0.06975 -0.0346 0.0178 1.0000
16.500 1.3642 0.07809 0.07310 -0.0354 0.0175 1.0000
16.750 1.3660 0.08144 0.07657 -0.0362 0.0173 1.0000
17.000 1.3668 0.08499 0.08023 -0.0373 0.0170 1.0000
17.250 1.3669 0.08871 0.08407 -0.0385 0.0168 1.0000
17.500 1.3663 0.09262 0.08810 -0.0399 0.0166 1.0000
17.750 1.3653 0.09665 0.09224 -0.0414 0.0164 1.0000
18.000 1.3637 0.10083 0.09652 -0.0431 0.0163 1.0000
18.250 1.3615 0.10515 0.10095 -0.0450 0.0161 1.0000
18.500 1.3595 0.10951 0.10541 -0.0470 0.0159 1.0000
18.750 1.3572 0.11393 0.10991 -0.0491 0.0158 1.0000
19.000 1.3540 0.11852 0.11460 -0.0514 0.0156 1.0000
19.250 1.3489 0.12347 0.11966 -0.0538 0.0154 1.0000
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