NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 50,000 Max Cl/Cd: 18.93 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415a05-il-50000-n5.txt Download as CSV file: xf-naca652415a05-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3834 0.10667 0.09996 -0.0626 1.0000 0.0633
-11.250 -0.3882 0.10389 0.09726 -0.0623 1.0000 0.0629
-11.000 -0.4035 0.10165 0.09515 -0.0609 1.0000 0.0627
-10.750 -0.4040 0.09643 0.08993 -0.0649 0.9897 0.0624
-10.500 -0.4052 0.08917 0.08263 -0.0722 0.9805 0.0622
-10.250 -0.4076 0.08249 0.07589 -0.0792 0.9721 0.0616
-10.000 -0.4171 0.07597 0.06924 -0.0861 0.9625 0.0612
-9.750 -0.4289 0.07083 0.06394 -0.0906 0.9515 0.0609
-9.500 -0.4419 0.06697 0.05987 -0.0920 0.9394 0.0607
-9.250 -0.4517 0.06351 0.05616 -0.0922 0.9286 0.0606
-9.000 -0.4565 0.06014 0.05246 -0.0920 0.9198 0.0606
-8.750 -0.4608 0.05725 0.04924 -0.0906 0.9104 0.0605
-8.500 -0.4610 0.05450 0.04612 -0.0892 0.9023 0.0606
-8.250 -0.4579 0.05189 0.04312 -0.0876 0.8946 0.0610
-8.000 -0.4525 0.04956 0.04033 -0.0858 0.8878 0.0620
-7.750 -0.4470 0.04759 0.03786 -0.0836 0.8805 0.0632
-7.500 -0.4290 0.04524 0.03525 -0.0832 0.8760 0.0648
-7.250 -0.4179 0.04368 0.03348 -0.0814 0.8692 0.0659
-7.000 -0.3992 0.04195 0.03147 -0.0805 0.8639 0.0670
-6.750 -0.3745 0.04025 0.02948 -0.0804 0.8602 0.0690
-6.500 -0.3598 0.03920 0.02818 -0.0787 0.8542 0.0717
-6.250 -0.3385 0.03805 0.02669 -0.0777 0.8493 0.0744
-6.000 -0.3087 0.03663 0.02510 -0.0780 0.8460 0.0768
-5.750 -0.2764 0.03542 0.02384 -0.0787 0.8433 0.0805
-5.500 -0.2615 0.03497 0.02330 -0.0767 0.8371 0.0845
-5.250 -0.2373 0.03432 0.02246 -0.0760 0.8329 0.0897
-5.000 -0.2134 0.03352 0.02167 -0.0755 0.8296 0.0947
-4.750 -0.1890 0.03289 0.02087 -0.0750 0.8268 0.1029
-4.500 -0.1859 0.03271 0.02075 -0.0716 0.8201 0.1093
-4.250 -0.1705 0.03219 0.02019 -0.0699 0.8157 0.1207
-4.000 -0.1522 0.03137 0.01949 -0.0689 0.8123 0.1437
-3.750 -0.1447 0.03045 0.01902 -0.0665 0.8079 0.2026
-3.500 -0.1520 0.02921 0.01910 -0.0617 0.8023 0.4023
-3.250 -0.1425 0.02929 0.01992 -0.0568 0.7986 0.6184
-3.000 -0.1255 0.02991 0.02063 -0.0526 0.7956 0.7091
-2.750 -0.1178 0.03116 0.02199 -0.0457 0.7917 0.7862
-2.500 -0.0833 0.03287 0.02361 -0.0424 0.7889 0.8474
-2.250 -0.0580 0.03319 0.02370 -0.0422 0.7852 0.8634
-2.000 -0.0290 0.03333 0.02361 -0.0428 0.7820 0.8756
-1.750 -0.0007 0.03338 0.02344 -0.0434 0.7794 0.8873
-1.500 0.0378 0.03352 0.02334 -0.0460 0.7770 0.8954
-1.250 0.0480 0.03402 0.02376 -0.0445 0.7715 0.9082
-1.000 0.0723 0.03427 0.02387 -0.0450 0.7678 0.9198
-0.750 0.1135 0.03447 0.02389 -0.0484 0.7652 0.9274
-0.500 0.1511 0.03461 0.02389 -0.0510 0.7629 0.9364
-0.250 0.1879 0.03496 0.02411 -0.0539 0.7601 0.9451
0.000 0.2115 0.03560 0.02470 -0.0553 0.7550 0.9565
0.250 0.2466 0.03598 0.02499 -0.0581 0.7515 0.9663
0.500 0.2854 0.03627 0.02521 -0.0613 0.7488 0.9754
0.750 0.3273 0.03652 0.02539 -0.0650 0.7466 0.9841
1.000 0.3594 0.03711 0.02594 -0.0678 0.7427 0.9958
1.250 0.3460 0.03780 0.02663 -0.0629 0.7360 1.0000
1.500 0.3502 0.03807 0.02685 -0.0599 0.7319 1.0000
1.750 0.3638 0.03831 0.02703 -0.0581 0.7288 1.0000
2.000 0.3246 0.03909 0.02775 -0.0490 0.7200 1.0000
2.250 0.3386 0.03950 0.02809 -0.0474 0.7161 1.0000
2.500 0.3630 0.03988 0.02841 -0.0473 0.7134 1.0000
2.750 0.3515 0.04086 0.02933 -0.0427 0.7055 1.0000
3.000 0.3705 0.04145 0.02989 -0.0421 0.7011 1.0000
3.250 0.3982 0.04192 0.03034 -0.0425 0.6980 1.0000
3.750 0.4188 0.04361 0.03201 -0.0394 0.6856 1.0000
4.000 0.4476 0.04412 0.03255 -0.0399 0.6822 1.0000
4.250 0.4516 0.04519 0.03363 -0.0377 0.6743 1.0000
4.500 0.4739 0.04586 0.03433 -0.0375 0.6691 1.0000
4.750 0.5057 0.04629 0.03482 -0.0383 0.6656 1.0000
5.000 0.5067 0.04753 0.03609 -0.0360 0.6561 1.0000
5.250 0.5352 0.04802 0.03666 -0.0364 0.6515 1.0000
5.500 0.5441 0.04910 0.03779 -0.0349 0.6429 1.0000
5.750 0.5690 0.04966 0.03846 -0.0349 0.6370 1.0000
6.000 0.5838 0.05057 0.03945 -0.0340 0.6289 1.0000
6.250 0.6061 0.05119 0.04018 -0.0337 0.6217 1.0000
6.500 0.6218 0.05202 0.04112 -0.0329 0.6130 1.0000
6.750 0.6462 0.05249 0.04173 -0.0326 0.6056 1.0000
7.000 0.6589 0.05341 0.04277 -0.0315 0.5952 1.0000
7.250 0.6900 0.05346 0.04299 -0.0316 0.5888 1.0000
7.500 0.7000 0.05442 0.04410 -0.0303 0.5766 1.0000
7.750 0.7187 0.05494 0.04478 -0.0295 0.5663 1.0000
8.000 0.7486 0.05472 0.04477 -0.0291 0.5579 1.0000
8.250 0.7614 0.05537 0.04560 -0.0278 0.5446 1.0000
8.500 0.7775 0.05575 0.04618 -0.0266 0.5313 1.0000
8.750 0.7969 0.05563 0.04627 -0.0253 0.5168 1.0000
9.000 0.8211 0.05461 0.04548 -0.0237 0.5001 1.0000
9.250 0.8418 0.05324 0.04434 -0.0214 0.4772 1.0000
9.500 0.8578 0.05186 0.04313 -0.0187 0.4466 1.0000
9.750 0.8751 0.05050 0.04189 -0.0161 0.4060 1.0000
10.000 0.9017 0.04839 0.03962 -0.0132 0.3360 1.0000
10.250 0.9134 0.04826 0.03860 -0.0101 0.2369 1.0000
10.500 0.9057 0.05112 0.04094 -0.0083 0.1796 1.0000
10.750 0.8992 0.05422 0.04363 -0.0070 0.1421 1.0000
11.000 0.8960 0.05717 0.04628 -0.0060 0.1196 1.0000
11.250 0.8972 0.05979 0.04874 -0.0051 0.1041 1.0000
11.500 0.9009 0.06220 0.05106 -0.0044 0.0929 1.0000
11.750 0.9096 0.06415 0.05308 -0.0035 0.0843 1.0000
12.000 0.9187 0.06606 0.05496 -0.0027 0.0778 1.0000
12.250 0.9322 0.06760 0.05660 -0.0019 0.0719 1.0000
12.500 0.9491 0.06882 0.05775 -0.0009 0.0676 1.0000
12.750 0.9710 0.06982 0.05901 0.0001 0.0633 1.0000
13.000 0.9916 0.07098 0.06026 0.0009 0.0592 1.0000
13.250 1.0237 0.07168 0.06106 0.0019 0.0564 1.0000
13.500 1.0468 0.07354 0.06327 0.0026 0.0543 1.0000
13.750 1.0604 0.07607 0.06608 0.0030 0.0524 1.0000
14.000 1.0691 0.07886 0.06909 0.0032 0.0507 1.0000
14.250 1.0773 0.08162 0.07198 0.0033 0.0492 1.0000
14.500 1.0863 0.08471 0.07516 0.0033 0.0480 1.0000
14.750 1.0785 0.08910 0.07991 0.0029 0.0476 1.0000
15.000 1.0677 0.09392 0.08505 0.0022 0.0474 1.0000
15.250 1.0540 0.09919 0.09061 0.0009 0.0473 1.0000
15.500 1.0374 0.10502 0.09672 -0.0009 0.0473 1.0000
15.750 1.0188 0.11146 0.10341 -0.0035 0.0473 1.0000
16.000 0.9973 0.11881 0.11098 -0.0070 0.0474 1.0000
16.250 0.9751 0.12691 0.11926 -0.0113 0.0476 1.0000
16.500 0.9536 0.13569 0.12818 -0.0164 0.0479 1.0000
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Polar data table (+)
Polar graphs
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