USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 200,000 Max Cl/Cd: 75.17 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35b-il-200000-n5.txt Download as CSV file: xf-usa35b-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3519 0.08850 0.08474 -0.0415 1.0000 0.0389
-10.250 -0.3528 0.08581 0.08211 -0.0414 1.0000 0.0387
-10.000 -0.3580 0.08349 0.07985 -0.0404 1.0000 0.0384
-9.750 -0.3530 0.07989 0.07628 -0.0430 0.9948 0.0380
-9.500 -0.3405 0.07445 0.07084 -0.0501 0.9847 0.0373
-9.250 -0.3267 0.06728 0.06362 -0.0605 0.9733 0.0366
-9.000 -0.3139 0.05739 0.05357 -0.0735 0.9606 0.0359
-8.750 -0.3013 0.04756 0.04343 -0.0833 0.9483 0.0361
-8.500 -0.2903 0.03780 0.03305 -0.0895 0.9369 0.0363
-8.250 -0.2726 0.03153 0.02612 -0.0921 0.9278 0.0363
-8.000 -0.2524 0.02798 0.02207 -0.0927 0.9174 0.0365
-7.750 -0.2270 0.02535 0.01898 -0.0934 0.9095 0.0369
-7.500 -0.2030 0.02343 0.01670 -0.0933 0.8987 0.0374
-7.250 -0.1768 0.02191 0.01481 -0.0933 0.8888 0.0382
-7.000 -0.1501 0.02064 0.01320 -0.0931 0.8783 0.0388
-6.750 -0.1239 0.01959 0.01188 -0.0928 0.8668 0.0392
-6.500 -0.0973 0.01861 0.01079 -0.0926 0.8558 0.0397
-6.250 -0.0705 0.01784 0.00991 -0.0923 0.8437 0.0401
-6.000 -0.0439 0.01717 0.00915 -0.0919 0.8301 0.0407
-5.750 -0.0172 0.01658 0.00845 -0.0916 0.8161 0.0413
-5.500 0.0096 0.01603 0.00780 -0.0912 0.8019 0.0420
-5.250 0.0365 0.01552 0.00718 -0.0908 0.7876 0.0428
-5.000 0.0634 0.01509 0.00664 -0.0904 0.7724 0.0440
-4.750 0.0904 0.01474 0.00615 -0.0900 0.7564 0.0453
-4.500 0.1170 0.01433 0.00570 -0.0897 0.7406 0.0466
-4.250 0.1439 0.01402 0.00534 -0.0893 0.7254 0.0479
-4.000 0.1709 0.01375 0.00500 -0.0890 0.7106 0.0495
-3.750 0.1981 0.01352 0.00467 -0.0887 0.6967 0.0513
-3.500 0.2253 0.01330 0.00438 -0.0884 0.6840 0.0536
-3.250 0.2526 0.01315 0.00417 -0.0882 0.6721 0.0571
-3.000 0.2797 0.01301 0.00397 -0.0879 0.6590 0.0631
-2.750 0.3069 0.01288 0.00380 -0.0876 0.6459 0.0729
-2.500 0.3342 0.01274 0.00365 -0.0874 0.6344 0.0892
-2.250 0.3615 0.01262 0.00353 -0.0872 0.6250 0.1124
-2.000 0.3888 0.01240 0.00350 -0.0872 0.6167 0.1619
-1.750 0.4159 0.01222 0.00348 -0.0871 0.6088 0.2321
-1.500 0.4415 0.01163 0.00353 -0.0870 0.6015 0.4209
-1.250 0.4625 0.01086 0.00365 -0.0854 0.5942 0.6800
-1.000 0.4987 0.01038 0.00367 -0.0860 0.5873 0.9785
-0.750 0.5297 0.01047 0.00366 -0.0866 0.5797 1.0000
-0.500 0.5567 0.01062 0.00368 -0.0863 0.5729 1.0000
-0.250 0.5839 0.01074 0.00372 -0.0861 0.5657 1.0000
0.000 0.6110 0.01087 0.00377 -0.0858 0.5588 1.0000
0.250 0.6381 0.01102 0.00383 -0.0855 0.5522 1.0000
0.500 0.6653 0.01114 0.00391 -0.0853 0.5445 1.0000
0.750 0.6923 0.01131 0.00398 -0.0850 0.5377 1.0000
1.000 0.7195 0.01143 0.00409 -0.0848 0.5303 1.0000
1.250 0.7464 0.01159 0.00419 -0.0845 0.5229 1.0000
1.500 0.7734 0.01174 0.00431 -0.0842 0.5149 1.0000
1.750 0.8001 0.01190 0.00443 -0.0839 0.5064 1.0000
2.000 0.8266 0.01205 0.00455 -0.0836 0.4953 1.0000
2.250 0.8524 0.01221 0.00465 -0.0831 0.4814 1.0000
2.500 0.8780 0.01239 0.00476 -0.0826 0.4658 1.0000
2.750 0.9037 0.01258 0.00490 -0.0821 0.4518 1.0000
3.000 0.9294 0.01278 0.00506 -0.0817 0.4390 1.0000
3.250 0.9552 0.01298 0.00525 -0.0812 0.4259 1.0000
3.500 0.9807 0.01321 0.00546 -0.0808 0.4131 1.0000
3.750 1.0058 0.01347 0.00567 -0.0802 0.4003 1.0000
4.000 1.0306 0.01374 0.00591 -0.0797 0.3874 1.0000
4.250 1.0550 0.01405 0.00618 -0.0790 0.3744 1.0000
4.500 1.0794 0.01436 0.00646 -0.0784 0.3617 1.0000
4.750 1.1034 0.01470 0.00678 -0.0778 0.3495 1.0000
5.000 1.1269 0.01507 0.00711 -0.0771 0.3375 1.0000
5.250 1.1498 0.01548 0.00749 -0.0763 0.3253 1.0000
5.500 1.1723 0.01590 0.00787 -0.0754 0.3109 1.0000
5.750 1.1942 0.01635 0.00829 -0.0745 0.2951 1.0000
6.000 1.2153 0.01684 0.00873 -0.0735 0.2783 1.0000
6.250 1.2362 0.01734 0.00919 -0.0725 0.2618 1.0000
6.500 1.2569 0.01784 0.00967 -0.0714 0.2465 1.0000
6.750 1.2771 0.01835 0.01018 -0.0703 0.2320 1.0000
7.000 1.2965 0.01891 0.01071 -0.0691 0.2178 1.0000
7.250 1.3145 0.01954 0.01130 -0.0678 0.2031 1.0000
7.500 1.3317 0.02019 0.01193 -0.0663 0.1901 1.0000
7.750 1.3483 0.02086 0.01260 -0.0647 0.1796 1.0000
8.000 1.3625 0.02158 0.01331 -0.0629 0.1706 1.0000
8.250 1.3769 0.02226 0.01402 -0.0610 0.1625 1.0000
8.500 1.3892 0.02307 0.01484 -0.0589 0.1538 1.0000
8.750 1.4005 0.02398 0.01576 -0.0569 0.1443 1.0000
9.000 1.4133 0.02482 0.01666 -0.0551 0.1358 1.0000
9.250 1.4236 0.02585 0.01770 -0.0532 0.1272 1.0000
9.500 1.4330 0.02699 0.01885 -0.0514 0.1164 1.0000
9.750 1.4417 0.02822 0.02010 -0.0496 0.1040 1.0000
10.000 1.4478 0.02971 0.02157 -0.0478 0.0861 1.0000
10.250 1.4473 0.03180 0.02354 -0.0458 0.0679 1.0000
10.500 1.4473 0.03398 0.02567 -0.0441 0.0606 1.0000
10.750 1.4484 0.03617 0.02791 -0.0427 0.0564 1.0000
11.000 1.4483 0.03859 0.03038 -0.0415 0.0534 1.0000
11.250 1.4506 0.04087 0.03278 -0.0406 0.0511 1.0000
11.500 1.4508 0.04347 0.03549 -0.0399 0.0491 1.0000
11.750 1.4485 0.04642 0.03853 -0.0394 0.0474 1.0000
12.000 1.4438 0.04977 0.04196 -0.0391 0.0461 1.0000
12.250 1.4441 0.05260 0.04494 -0.0389 0.0448 1.0000
12.500 1.4426 0.05573 0.04819 -0.0388 0.0435 1.0000
12.750 1.4396 0.05910 0.05168 -0.0389 0.0423 1.0000
13.000 1.4350 0.06275 0.05544 -0.0392 0.0413 1.0000
13.250 1.4285 0.06671 0.05951 -0.0396 0.0404 1.0000
13.500 1.4201 0.07102 0.06390 -0.0403 0.0396 1.0000
13.750 1.4154 0.07491 0.06790 -0.0409 0.0388 1.0000
14.000 1.4120 0.07868 0.07181 -0.0415 0.0379 1.0000
14.250 1.4077 0.08265 0.07589 -0.0423 0.0370 1.0000
14.500 1.4030 0.08676 0.08011 -0.0432 0.0362 1.0000
14.750 1.3978 0.09096 0.08441 -0.0442 0.0354 1.0000
15.000 1.3921 0.09528 0.08882 -0.0453 0.0347 1.0000
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