USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 500,000 Max Cl/Cd: 106.04 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35b-il-500000.txt Download as CSV file: xf-usa35b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA-35B 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3628 0.11786 0.11536 -0.0251 1.0000 0.0316
-12.250 -0.3577 0.11453 0.11204 -0.0266 1.0000 0.0326
-12.000 -0.3766 0.10665 0.10418 -0.0354 1.0000 0.0342
-11.750 -0.3694 0.10338 0.10092 -0.0348 1.0000 0.0345
-11.500 -0.3599 0.10099 0.09855 -0.0347 1.0000 0.0347
-11.250 -0.3508 0.09861 0.09619 -0.0349 1.0000 0.0349
-11.000 -0.3430 0.09609 0.09369 -0.0354 1.0000 0.0353
-10.750 -0.3370 0.09340 0.09101 -0.0362 1.0000 0.0358
-10.500 -0.3328 0.09056 0.08819 -0.0372 1.0000 0.0364
-10.250 -0.2677 0.07226 0.07009 -0.0491 0.9943 0.0400
-10.000 -0.2517 0.06915 0.06699 -0.0508 0.9913 0.0403
-9.750 -0.2365 0.06580 0.06364 -0.0532 0.9875 0.0408
-9.500 -0.2233 0.06190 0.05974 -0.0566 0.9832 0.0414
-9.250 -0.2156 0.05760 0.05544 -0.0602 0.9744 0.0422
-9.000 -0.2571 0.03532 0.03273 -0.0883 0.9560 0.0460
-8.750 -0.2419 0.03335 0.03079 -0.0878 0.9457 0.0464
-8.500 -0.2265 0.03134 0.02876 -0.0877 0.9359 0.0468
-8.250 -0.2115 0.02931 0.02666 -0.0876 0.9251 0.0472
-8.000 -0.1963 0.02708 0.02435 -0.0878 0.9133 0.0480
-7.750 -0.2189 0.02295 0.01812 -0.0951 0.9244 0.0399
-7.500 -0.1953 0.02148 0.01651 -0.0944 0.9138 0.0392
-7.250 -0.1725 0.01931 0.01406 -0.0939 0.9042 0.0389
-7.000 -0.1481 0.01790 0.01238 -0.0933 0.8935 0.0390
-6.750 -0.1224 0.01700 0.01124 -0.0928 0.8826 0.0393
-6.500 -0.0965 0.01605 0.01008 -0.0923 0.8717 0.0395
-6.250 -0.0704 0.01510 0.00895 -0.0918 0.8591 0.0396
-6.000 -0.0446 0.01393 0.00763 -0.0914 0.8455 0.0399
-5.750 -0.0184 0.01308 0.00669 -0.0909 0.8313 0.0404
-5.500 0.0082 0.01250 0.00603 -0.0905 0.8162 0.0409
-5.250 0.0350 0.01206 0.00551 -0.0901 0.7995 0.0415
-5.000 0.0618 0.01169 0.00506 -0.0897 0.7809 0.0422
-4.750 0.0888 0.01141 0.00468 -0.0893 0.7610 0.0433
-4.500 0.1157 0.01117 0.00432 -0.0890 0.7409 0.0444
-4.250 0.1427 0.01095 0.00398 -0.0886 0.7200 0.0452
-4.000 0.1696 0.01068 0.00359 -0.0882 0.6990 0.0461
-3.750 0.1963 0.01039 0.00323 -0.0879 0.6804 0.0477
-3.500 0.2238 0.01026 0.00303 -0.0877 0.6655 0.0494
-3.250 0.2515 0.01016 0.00285 -0.0875 0.6538 0.0517
-3.000 0.2793 0.01000 0.00265 -0.0874 0.6431 0.0550
-2.750 0.3074 0.00992 0.00254 -0.0873 0.6339 0.0605
-2.500 0.3353 0.00975 0.00240 -0.0872 0.6254 0.0750
-2.250 0.3633 0.00954 0.00230 -0.0872 0.6176 0.1119
-2.000 0.3910 0.00930 0.00228 -0.0872 0.6098 0.1869
-1.750 0.4186 0.00908 0.00227 -0.0872 0.6030 0.2658
-1.500 0.4454 0.00855 0.00232 -0.0873 0.5962 0.4554
-1.250 0.4708 0.00809 0.00239 -0.0869 0.5897 0.6416
-1.000 0.4880 0.00743 0.00252 -0.0839 0.5837 0.9024
-0.750 0.5335 0.00741 0.00248 -0.0874 0.5763 1.0000
-0.500 0.5608 0.00754 0.00251 -0.0872 0.5705 1.0000
-0.250 0.5886 0.00760 0.00254 -0.0870 0.5641 1.0000
0.000 0.6161 0.00771 0.00257 -0.0868 0.5575 1.0000
0.250 0.6437 0.00781 0.00262 -0.0866 0.5512 1.0000
0.500 0.6715 0.00789 0.00267 -0.0865 0.5446 1.0000
1.000 0.7264 0.00809 0.00276 -0.0861 0.5274 1.0000
1.250 0.7536 0.00820 0.00281 -0.0858 0.5171 1.0000
1.500 0.7810 0.00831 0.00287 -0.0856 0.5073 1.0000
1.750 0.8084 0.00841 0.00294 -0.0854 0.4976 1.0000
2.000 0.8355 0.00855 0.00302 -0.0852 0.4880 1.0000
2.250 0.8630 0.00865 0.00311 -0.0850 0.4780 1.0000
2.500 0.8901 0.00879 0.00321 -0.0848 0.4682 1.0000
2.750 0.9171 0.00893 0.00332 -0.0846 0.4571 1.0000
3.000 0.9442 0.00907 0.00344 -0.0844 0.4453 1.0000
3.250 0.9709 0.00924 0.00357 -0.0841 0.4328 1.0000
3.500 0.9972 0.00944 0.00372 -0.0838 0.4191 1.0000
3.750 1.0233 0.00965 0.00388 -0.0834 0.4046 1.0000
4.000 1.0491 0.00990 0.00407 -0.0830 0.3896 1.0000
4.250 1.0745 0.01017 0.00428 -0.0826 0.3727 1.0000
4.500 1.0995 0.01048 0.00451 -0.0821 0.3554 1.0000
4.750 1.1243 0.01080 0.00476 -0.0816 0.3394 1.0000
5.000 1.1489 0.01113 0.00504 -0.0810 0.3248 1.0000
5.250 1.1734 0.01147 0.00532 -0.0805 0.3117 1.0000
5.500 1.1983 0.01177 0.00560 -0.0800 0.2986 1.0000
5.750 1.2224 0.01212 0.00591 -0.0794 0.2831 1.0000
6.000 1.2462 0.01250 0.00623 -0.0788 0.2670 1.0000
6.250 1.2695 0.01289 0.00656 -0.0781 0.2507 1.0000
6.500 1.2921 0.01334 0.00694 -0.0773 0.2330 1.0000
6.750 1.3141 0.01381 0.00734 -0.0765 0.2139 1.0000
7.000 1.3352 0.01434 0.00779 -0.0755 0.1959 1.0000
7.250 1.3556 0.01490 0.00828 -0.0744 0.1804 1.0000
7.500 1.3759 0.01544 0.00878 -0.0733 0.1684 1.0000
7.750 1.3956 0.01600 0.00930 -0.0722 0.1578 1.0000
8.000 1.4145 0.01658 0.00984 -0.0709 0.1474 1.0000
8.250 1.4338 0.01711 0.01036 -0.0696 0.1368 1.0000
8.500 1.4504 0.01779 0.01098 -0.0681 0.1226 1.0000
8.750 1.4628 0.01859 0.01169 -0.0658 0.1026 1.0000
9.000 1.4636 0.02006 0.01286 -0.0621 0.0653 1.0000
9.250 1.4687 0.02134 0.01407 -0.0591 0.0553 1.0000
9.500 1.4763 0.02250 0.01525 -0.0567 0.0510 1.0000
9.750 1.4838 0.02372 0.01652 -0.0544 0.0480 1.0000
10.000 1.4936 0.02483 0.01771 -0.0525 0.0459 1.0000
10.250 1.5003 0.02621 0.01915 -0.0506 0.0440 1.0000
10.500 1.5017 0.02808 0.02107 -0.0484 0.0421 1.0000
10.750 1.5100 0.02951 0.02258 -0.0470 0.0408 1.0000
11.000 1.5172 0.03108 0.02425 -0.0457 0.0395 1.0000
11.250 1.5223 0.03291 0.02615 -0.0444 0.0383 1.0000
11.500 1.5244 0.03511 0.02842 -0.0433 0.0372 1.0000
11.750 1.5209 0.03796 0.03135 -0.0422 0.0362 1.0000
12.000 1.5195 0.04074 0.03423 -0.0415 0.0353 1.0000
12.250 1.5244 0.04296 0.03656 -0.0410 0.0345 1.0000
12.500 1.5265 0.04553 0.03922 -0.0406 0.0336 1.0000
12.750 1.5270 0.04835 0.04213 -0.0404 0.0327 1.0000
13.000 1.5256 0.05143 0.04529 -0.0403 0.0320 1.0000
13.250 1.5213 0.05492 0.04886 -0.0403 0.0314 1.0000
13.500 1.5125 0.05901 0.05302 -0.0405 0.0308 1.0000
13.750 1.5032 0.06318 0.05727 -0.0406 0.0302 1.0000
14.000 1.5033 0.06635 0.06056 -0.0409 0.0297 1.0000
14.250 1.5018 0.06977 0.06409 -0.0413 0.0291 1.0000
14.500 1.4991 0.07339 0.06781 -0.0418 0.0285 1.0000
14.750 1.4956 0.07713 0.07164 -0.0424 0.0280 1.0000
15.000 1.4918 0.08098 0.07557 -0.0432 0.0274 1.0000
15.250 1.4873 0.08497 0.07963 -0.0440 0.0269 1.0000
15.500 1.4817 0.08914 0.08385 -0.0449 0.0264 1.0000
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