NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-415 AIRFOIL (n63415-il) Reynolds number: 100,000 Max Cl/Cd: 52.33 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63415-il-100000-n5.txt Download as CSV file: xf-n63415-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5886 0.08097 0.07539 -0.0602 1.0000 0.0375
-12.500 -0.6408 0.06938 0.06356 -0.0684 1.0000 0.0367
-12.250 -0.6757 0.06224 0.05619 -0.0725 1.0000 0.0362
-12.000 -0.6959 0.05773 0.05149 -0.0743 1.0000 0.0364
-11.750 -0.7103 0.05431 0.04792 -0.0749 1.0000 0.0368
-11.500 -0.7250 0.05121 0.04464 -0.0746 1.0000 0.0372
-11.250 -0.7391 0.04862 0.04189 -0.0731 1.0000 0.0375
-11.000 -0.7535 0.04652 0.03964 -0.0704 1.0000 0.0379
-10.750 -0.7635 0.04445 0.03737 -0.0676 1.0000 0.0384
-10.500 -0.7711 0.04255 0.03528 -0.0645 1.0000 0.0388
-10.250 -0.7788 0.04094 0.03347 -0.0609 1.0000 0.0393
-10.000 -0.7773 0.03901 0.03123 -0.0588 0.9972 0.0400
-9.750 -0.7503 0.03684 0.02887 -0.0610 0.9886 0.0415
-9.500 -0.7211 0.03527 0.02720 -0.0632 0.9809 0.0434
-9.250 -0.6912 0.03348 0.02518 -0.0651 0.9736 0.0454
-9.000 -0.6615 0.03172 0.02311 -0.0666 0.9660 0.0474
-8.750 -0.6290 0.03018 0.02152 -0.0685 0.9602 0.0496
-8.500 -0.5993 0.02902 0.02031 -0.0700 0.9524 0.0523
-8.250 -0.5670 0.02778 0.01891 -0.0715 0.9458 0.0552
-8.000 -0.5384 0.02664 0.01772 -0.0724 0.9379 0.0580
-7.750 -0.5088 0.02565 0.01672 -0.0736 0.9303 0.0618
-7.500 -0.4809 0.02476 0.01572 -0.0742 0.9221 0.0655
-7.250 -0.4545 0.02381 0.01478 -0.0748 0.9139 0.0697
-7.000 -0.4294 0.02305 0.01397 -0.0749 0.9052 0.0748
-6.750 -0.4046 0.02222 0.01310 -0.0751 0.8968 0.0804
-6.500 -0.3815 0.02155 0.01237 -0.0749 0.8879 0.0886
-6.250 -0.3572 0.02075 0.01160 -0.0750 0.8799 0.0998
-6.000 -0.3349 0.02003 0.01091 -0.0746 0.8710 0.1176
-5.750 -0.3116 0.01914 0.01020 -0.0747 0.8633 0.1519
-5.500 -0.2906 0.01820 0.00955 -0.0745 0.8549 0.2125
-5.250 -0.2688 0.01722 0.00904 -0.0744 0.8471 0.3084
-5.000 -0.2453 0.01675 0.00894 -0.0740 0.8397 0.3970
-4.750 -0.2199 0.01663 0.00890 -0.0735 0.8320 0.4532
-4.500 -0.1921 0.01662 0.00890 -0.0732 0.8262 0.4940
-4.250 -0.1673 0.01673 0.00900 -0.0725 0.8177 0.5248
-4.000 -0.1399 0.01684 0.00904 -0.0720 0.8115 0.5501
-3.750 -0.1137 0.01695 0.00907 -0.0714 0.8042 0.5695
-3.500 -0.0873 0.01705 0.00910 -0.0708 0.7972 0.5854
-3.250 -0.0596 0.01714 0.00911 -0.0703 0.7918 0.5998
-3.000 -0.0344 0.01723 0.00916 -0.0697 0.7837 0.6116
-2.750 -0.0060 0.01717 0.00895 -0.0698 0.7777 0.6225
-2.500 0.0202 0.01721 0.00897 -0.0692 0.7711 0.6295
-2.250 0.0477 0.01717 0.00883 -0.0692 0.7641 0.6390
-2.000 0.0755 0.01715 0.00874 -0.0688 0.7590 0.6456
-1.750 0.1017 0.01718 0.00872 -0.0687 0.7514 0.6539
-1.500 0.1291 0.01716 0.00864 -0.0685 0.7453 0.6608
-1.250 0.1568 0.01715 0.00857 -0.0683 0.7398 0.6679
-1.000 0.1836 0.01716 0.00854 -0.0684 0.7324 0.6757
-0.750 0.2109 0.01716 0.00851 -0.0680 0.7270 0.6817
-0.500 0.2384 0.01717 0.00848 -0.0681 0.7207 0.6895
-0.250 0.2647 0.01721 0.00852 -0.0678 0.7141 0.6958
0.000 0.2929 0.01720 0.00846 -0.0677 0.7091 0.7027
0.250 0.3196 0.01727 0.00853 -0.0677 0.7024 0.7104
0.500 0.3457 0.01731 0.00859 -0.0672 0.6962 0.7166
0.750 0.3752 0.01730 0.00852 -0.0675 0.6916 0.7248
1.000 0.3995 0.01743 0.00873 -0.0669 0.6844 0.7311
1.250 0.4267 0.01748 0.00877 -0.0668 0.6786 0.7388
1.500 0.4545 0.01750 0.00879 -0.0667 0.6738 0.7460
1.750 0.4787 0.01766 0.00902 -0.0661 0.6666 0.7534
2.000 0.5063 0.01771 0.00908 -0.0661 0.6612 0.7615
2.250 0.5322 0.01779 0.00921 -0.0656 0.6557 0.7686
2.500 0.5579 0.01794 0.00943 -0.0654 0.6487 0.7774
2.750 0.5841 0.01798 0.00950 -0.0649 0.6435 0.7845
3.000 0.6101 0.01814 0.00973 -0.0647 0.6369 0.7938
3.250 0.6340 0.01825 0.00993 -0.0639 0.6303 0.8014
3.500 0.6630 0.01827 0.00995 -0.0639 0.6253 0.8108
3.750 0.6843 0.01849 0.01032 -0.0628 0.6173 0.8193
4.000 0.7110 0.01855 0.01043 -0.0625 0.6112 0.8289
4.250 0.7347 0.01869 0.01066 -0.0617 0.6043 0.8385
4.500 0.7583 0.01880 0.01089 -0.0609 0.5969 0.8483
4.750 0.7845 0.01884 0.01099 -0.0604 0.5903 0.8594
5.000 0.8051 0.01896 0.01124 -0.0591 0.5812 0.8703
5.250 0.8285 0.01894 0.01131 -0.0580 0.5724 0.8820
5.500 0.8509 0.01891 0.01136 -0.0567 0.5618 0.8953
5.750 0.8712 0.01894 0.01152 -0.0553 0.5502 0.9106
6.000 0.8944 0.01889 0.01157 -0.0542 0.5388 0.9280
6.250 0.9208 0.01882 0.01157 -0.0539 0.5255 0.9496
6.500 0.9516 0.01882 0.01168 -0.0547 0.5083 1.0000
6.750 0.9757 0.01900 0.01193 -0.0545 0.4887 1.0000
7.000 0.9987 0.01915 0.01206 -0.0540 0.4635 1.0000
7.250 1.0184 0.01946 0.01232 -0.0530 0.4325 1.0000
7.500 1.0360 0.01991 0.01267 -0.0518 0.3956 1.0000
7.750 1.0507 0.02055 0.01314 -0.0502 0.3525 1.0000
8.000 1.0605 0.02147 0.01380 -0.0481 0.3060 1.0000
8.250 1.0648 0.02263 0.01469 -0.0453 0.2614 1.0000
8.500 1.0664 0.02402 0.01583 -0.0425 0.2214 1.0000
8.750 1.0680 0.02558 0.01718 -0.0401 0.1867 1.0000
9.000 1.0701 0.02724 0.01868 -0.0381 0.1574 1.0000
9.250 1.0726 0.02898 0.02029 -0.0363 0.1332 1.0000
9.500 1.0759 0.03078 0.02198 -0.0347 0.1134 1.0000
9.750 1.0795 0.03264 0.02377 -0.0334 0.0990 1.0000
10.000 1.0839 0.03452 0.02563 -0.0322 0.0882 1.0000
10.250 1.0880 0.03649 0.02758 -0.0311 0.0802 1.0000
10.500 1.0928 0.03846 0.02957 -0.0302 0.0738 1.0000
10.750 1.0977 0.04048 0.03162 -0.0293 0.0689 1.0000
11.000 1.1038 0.04245 0.03365 -0.0286 0.0646 1.0000
11.250 1.1074 0.04468 0.03585 -0.0280 0.0612 1.0000
11.500 1.1155 0.04657 0.03785 -0.0274 0.0576 1.0000
11.750 1.1220 0.04863 0.03996 -0.0269 0.0547 1.0000
12.000 1.1269 0.05088 0.04220 -0.0265 0.0523 1.0000
12.250 1.1360 0.05280 0.04428 -0.0261 0.0495 1.0000
12.500 1.1435 0.05489 0.04644 -0.0258 0.0472 1.0000
12.750 1.1501 0.05710 0.04866 -0.0256 0.0453 1.0000
13.000 1.1583 0.05923 0.05087 -0.0253 0.0435 1.0000
13.250 1.1672 0.06138 0.05319 -0.0250 0.0416 1.0000
13.500 1.1752 0.06363 0.05554 -0.0249 0.0400 1.0000
13.750 1.1826 0.06595 0.05791 -0.0249 0.0387 1.0000
14.000 1.1913 0.06817 0.06010 -0.0248 0.0374 1.0000
14.250 1.1969 0.07095 0.06312 -0.0249 0.0362 1.0000
14.500 1.2015 0.07388 0.06626 -0.0251 0.0350 1.0000
14.750 1.2051 0.07694 0.06949 -0.0255 0.0340 1.0000
15.000 1.2082 0.08009 0.07281 -0.0261 0.0332 1.0000
15.250 1.2111 0.08331 0.07616 -0.0267 0.0325 1.0000
15.500 1.2141 0.08656 0.07950 -0.0274 0.0320 1.0000
15.750 1.2182 0.08974 0.08275 -0.0280 0.0314 1.0000
16.000 1.2133 0.09432 0.08756 -0.0295 0.0311 1.0000
16.250 1.2031 0.09982 0.09336 -0.0316 0.0308 1.0000
16.500 1.1905 0.10592 0.09974 -0.0344 0.0305 1.0000
16.750 1.1746 0.11279 0.10690 -0.0380 0.0303 1.0000
17.000 1.1566 0.12040 0.11478 -0.0423 0.0302 1.0000
17.250 1.1347 0.12924 0.12388 -0.0477 0.0302 1.0000
17.500 1.1084 0.13971 0.13461 -0.0546 0.0303 1.0000
17.750 1.0727 0.15358 0.14873 -0.0640 0.0306 1.0000
18.000 1.0157 0.17632 0.17164 -0.0788 0.0311 1.0000
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Polar data table (+)
Polar graphs
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