NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 100,000 Max Cl/Cd: 28.42 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662215-il-100000-n5.txt Download as CSV file: xf-naca662215-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5077 0.10362 0.09826 -0.0650 1.0000 0.0360
-13.000 -0.5186 0.09675 0.09141 -0.0684 1.0000 0.0357
-12.750 -0.5359 0.08955 0.08420 -0.0725 1.0000 0.0353
-12.500 -0.5584 0.08304 0.07767 -0.0758 1.0000 0.0350
-12.250 -0.5859 0.07763 0.07221 -0.0773 1.0000 0.0348
-12.000 -0.6145 0.07405 0.06860 -0.0762 1.0000 0.0346
-11.750 -0.6414 0.07088 0.06536 -0.0747 0.9970 0.0344
-11.500 -0.6577 0.06577 0.06000 -0.0770 0.9874 0.0343
-11.250 -0.6705 0.06126 0.05519 -0.0784 0.9797 0.0342
-11.000 -0.6776 0.05724 0.05085 -0.0793 0.9731 0.0342
-10.750 -0.6833 0.05378 0.04705 -0.0789 0.9651 0.0342
-10.500 -0.6870 0.05079 0.04371 -0.0775 0.9570 0.0343
-10.250 -0.6842 0.04786 0.04039 -0.0764 0.9509 0.0346
-10.000 -0.6829 0.04553 0.03765 -0.0742 0.9437 0.0351
-9.750 -0.6773 0.04340 0.03504 -0.0723 0.9378 0.0359
-9.500 -0.6655 0.04113 0.03240 -0.0711 0.9333 0.0365
-9.250 -0.6518 0.03916 0.03026 -0.0699 0.9277 0.0372
-9.000 -0.6316 0.03726 0.02814 -0.0696 0.9238 0.0378
-8.750 -0.6070 0.03545 0.02609 -0.0699 0.9211 0.0384
-8.500 -0.5844 0.03394 0.02436 -0.0696 0.9175 0.0392
-8.250 -0.5620 0.03262 0.02288 -0.0691 0.9135 0.0401
-8.000 -0.5366 0.03145 0.02155 -0.0692 0.9104 0.0419
-7.750 -0.5078 0.03031 0.02020 -0.0697 0.9080 0.0438
-7.500 -0.4746 0.02907 0.01880 -0.0709 0.9063 0.0451
-7.250 -0.4409 0.02773 0.01751 -0.0725 0.9050 0.0467
-7.000 -0.4197 0.02699 0.01678 -0.0718 0.9016 0.0485
-6.750 -0.4034 0.02646 0.01621 -0.0702 0.8971 0.0510
-6.500 -0.3840 0.02589 0.01556 -0.0691 0.8935 0.0536
-6.250 -0.3658 0.02519 0.01482 -0.0679 0.8905 0.0558
-6.000 -0.3485 0.02459 0.01419 -0.0666 0.8879 0.0584
-5.750 -0.3434 0.02443 0.01401 -0.0630 0.8825 0.0612
-5.500 -0.3297 0.02415 0.01362 -0.0608 0.8788 0.0655
-5.250 -0.3146 0.02366 0.01316 -0.0590 0.8759 0.0718
-5.000 -0.2957 0.02319 0.01268 -0.0577 0.8737 0.0811
-4.750 -0.2864 0.02282 0.01245 -0.0548 0.8697 0.1015
-4.500 -0.2881 0.02221 0.01232 -0.0502 0.8644 0.1807
-4.250 -0.2944 0.02107 0.01202 -0.0449 0.8603 0.3400
-4.000 -0.2776 0.02110 0.01365 -0.0406 0.8588 0.6255
-3.750 -0.2666 0.02148 0.01395 -0.0371 0.8565 0.6910
-3.500 -0.2732 0.02228 0.01474 -0.0303 0.8506 0.7215
-3.250 -0.2490 0.02395 0.01638 -0.0271 0.8481 0.7573
-3.000 -0.2295 0.02500 0.01735 -0.0240 0.8456 0.7814
-2.750 -0.1901 0.02612 0.01837 -0.0244 0.8448 0.7961
-2.500 -0.1571 0.02645 0.01857 -0.0251 0.8436 0.8016
-2.250 -0.1291 0.02654 0.01855 -0.0253 0.8421 0.8060
-2.000 -0.1275 0.02643 0.01836 -0.0212 0.8385 0.8146
-1.500 -0.1054 0.02690 0.01872 -0.0157 0.8304 0.8241
-1.250 -0.0941 0.02671 0.01846 -0.0133 0.8274 0.8307
-1.000 -0.0629 0.02675 0.01843 -0.0141 0.8260 0.8330
-0.750 -0.0324 0.02676 0.01837 -0.0150 0.8246 0.8356
-0.500 -0.0616 0.02689 0.01851 -0.0053 0.8156 0.8443
-0.250 -0.0407 0.02687 0.01844 -0.0045 0.8127 0.8476
0.000 -0.0115 0.02688 0.01841 -0.0052 0.8107 0.8497
0.250 0.0195 0.02685 0.01835 -0.0061 0.8092 0.8519
0.750 0.0226 0.02689 0.01836 0.0019 0.7975 0.8618
1.000 0.0523 0.02691 0.01837 0.0012 0.7951 0.8635
1.250 0.0848 0.02688 0.01834 0.0000 0.7933 0.8651
1.750 0.1082 0.02714 0.01862 0.0045 0.7817 0.8716
2.000 0.1368 0.02706 0.01856 0.0040 0.7789 0.8743
2.250 0.1689 0.02693 0.01846 0.0029 0.7769 0.8769
2.500 0.1696 0.02730 0.01886 0.0069 0.7679 0.8806
2.750 0.1984 0.02729 0.01891 0.0064 0.7643 0.8825
3.000 0.2322 0.02719 0.01887 0.0051 0.7620 0.8843
3.500 0.2664 0.02737 0.01918 0.0078 0.7487 0.8916
3.750 0.3022 0.02713 0.01902 0.0064 0.7461 0.8938
4.000 0.3116 0.02741 0.01939 0.0090 0.7357 0.8977
4.500 0.3627 0.02725 0.01944 0.0094 0.7227 0.9038
4.750 0.3941 0.02690 0.01922 0.0089 0.7172 0.9065
5.250 0.4564 0.02568 0.01828 0.0089 0.7001 0.9117
5.500 0.4865 0.02423 0.01695 0.0102 0.6821 0.9146
5.750 0.4970 0.02350 0.01631 0.0138 0.6546 0.9208
6.000 0.4976 0.02369 0.01660 0.0178 0.6157 0.9280
6.250 0.5689 0.02002 0.01213 0.0163 0.4568 0.9259
6.500 0.5700 0.02103 0.01241 0.0203 0.3334 0.9322
6.750 0.5682 0.02245 0.01312 0.0238 0.2122 0.9395
7.000 0.5767 0.02394 0.01389 0.0256 0.1025 0.9452
7.250 0.5926 0.02488 0.01466 0.0266 0.0767 0.9515
7.500 0.6139 0.02578 0.01554 0.0266 0.0657 0.9564
7.750 0.6335 0.02670 0.01647 0.0267 0.0593 0.9630
8.000 0.6568 0.02765 0.01755 0.0261 0.0550 0.9685
8.250 0.6779 0.02873 0.01866 0.0257 0.0513 0.9753
8.500 0.7010 0.02977 0.01979 0.0250 0.0480 0.9825
8.750 0.7234 0.03073 0.02084 0.0246 0.0455 0.9940
9.000 0.7394 0.03166 0.02178 0.0255 0.0439 1.0000
9.250 0.7559 0.03267 0.02273 0.0264 0.0420 1.0000
9.500 0.7787 0.03372 0.02383 0.0267 0.0403 1.0000
9.750 0.8029 0.03478 0.02503 0.0267 0.0383 1.0000
10.000 0.8306 0.03606 0.02641 0.0264 0.0371 1.0000
10.250 0.8589 0.03752 0.02798 0.0259 0.0360 1.0000
10.500 0.8861 0.03912 0.02969 0.0254 0.0350 1.0000
10.750 0.9131 0.04102 0.03165 0.0246 0.0338 1.0000
11.000 0.9327 0.04315 0.03401 0.0249 0.0328 1.0000
11.250 0.9431 0.04507 0.03628 0.0262 0.0318 1.0000
11.500 0.9537 0.04735 0.03886 0.0273 0.0314 1.0000
11.750 0.9595 0.04983 0.04165 0.0288 0.0310 1.0000
12.000 0.9611 0.05247 0.04459 0.0305 0.0307 1.0000
12.250 0.9586 0.05529 0.04770 0.0323 0.0305 1.0000
12.500 0.9526 0.05827 0.05098 0.0341 0.0304 1.0000
12.750 0.9426 0.06153 0.05452 0.0358 0.0303 1.0000
13.000 0.9289 0.06513 0.05839 0.0372 0.0302 1.0000
13.250 0.9133 0.06901 0.06253 0.0382 0.0303 1.0000
13.500 0.8945 0.07337 0.06714 0.0386 0.0303 1.0000
13.750 0.8724 0.07836 0.07236 0.0382 0.0304 1.0000
14.000 0.8484 0.08400 0.07822 0.0370 0.0305 1.0000
14.250 0.8222 0.09053 0.08493 0.0344 0.0307 1.0000
14.500 0.7917 0.09881 0.09340 0.0301 0.0310 1.0000
14.750 0.7598 0.10909 0.10383 0.0238 0.0314 1.0000
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