USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.56 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35b-il-1000000.txt Download as CSV file: xf-usa35b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3499 0.08535 0.08368 -0.0390 1.0000 0.0269
-10.250 -0.3457 0.08175 0.08009 -0.0416 0.9978 0.0275
-10.000 -0.4231 0.03455 0.03202 -0.0918 0.9573 0.0298
-9.750 -0.4050 0.03290 0.03029 -0.0919 0.9474 0.0301
-9.500 -0.4101 0.02287 0.01937 -0.0928 0.9339 0.0274
-9.250 -0.3900 0.02084 0.01703 -0.0924 0.9249 0.0278
-9.000 -0.3686 0.01882 0.01469 -0.0920 0.9156 0.0279
-8.750 -0.3454 0.01740 0.01302 -0.0915 0.9067 0.0281
-8.500 -0.3207 0.01626 0.01168 -0.0912 0.8968 0.0283
-8.250 -0.2954 0.01533 0.01056 -0.0908 0.8875 0.0285
-8.000 -0.2695 0.01456 0.00963 -0.0905 0.8773 0.0287
-7.750 -0.2429 0.01394 0.00887 -0.0903 0.8674 0.0290
-7.500 -0.2162 0.01345 0.00824 -0.0900 0.8569 0.0292
-7.250 -0.1887 0.01313 0.00782 -0.0898 0.8454 0.0294
-7.000 -0.1634 0.01186 0.00641 -0.0895 0.8334 0.0301
-6.750 -0.1366 0.01135 0.00583 -0.0892 0.8202 0.0304
-6.500 -0.1095 0.01098 0.00538 -0.0890 0.8059 0.0308
-6.250 -0.0821 0.01064 0.00497 -0.0888 0.7905 0.0311
-6.000 -0.0548 0.01036 0.00459 -0.0886 0.7732 0.0315
-5.750 -0.0274 0.01009 0.00425 -0.0884 0.7531 0.0319
-5.500 0.0000 0.00987 0.00392 -0.0882 0.7300 0.0323
-5.250 0.0271 0.00970 0.00362 -0.0879 0.7060 0.0328
-5.000 0.0545 0.00955 0.00336 -0.0877 0.6817 0.0333
-4.750 0.0820 0.00944 0.00313 -0.0875 0.6595 0.0337
-4.500 0.1097 0.00936 0.00295 -0.0874 0.6419 0.0341
-4.250 0.1374 0.00905 0.00257 -0.0873 0.6287 0.0352
-4.000 0.1655 0.00892 0.00240 -0.0872 0.6181 0.0363
-3.750 0.1938 0.00881 0.00225 -0.0872 0.6089 0.0372
-3.500 0.2223 0.00872 0.00212 -0.0872 0.6012 0.0382
-3.250 0.2508 0.00864 0.00201 -0.0872 0.5934 0.0393
-3.000 0.2792 0.00853 0.00186 -0.0872 0.5863 0.0412
-2.750 0.3079 0.00843 0.00177 -0.0872 0.5798 0.0439
-2.500 0.3363 0.00836 0.00169 -0.0872 0.5734 0.0488
-2.250 0.3649 0.00822 0.00163 -0.0872 0.5677 0.0682
-2.000 0.3935 0.00811 0.00159 -0.0873 0.5614 0.0954
-1.750 0.4217 0.00801 0.00157 -0.0873 0.5552 0.1292
-1.500 0.4502 0.00781 0.00158 -0.0875 0.5503 0.1971
-1.250 0.4786 0.00768 0.00158 -0.0876 0.5447 0.2488
-1.000 0.5063 0.00739 0.00161 -0.0877 0.5388 0.3744
-0.750 0.5340 0.00702 0.00166 -0.0878 0.5335 0.5285
-0.500 0.5598 0.00649 0.00174 -0.0874 0.5278 0.7411
-0.250 0.5797 0.00606 0.00184 -0.0851 0.5224 0.9588
0.000 0.6198 0.00608 0.00183 -0.0876 0.5155 1.0000
0.250 0.6475 0.00618 0.00186 -0.0874 0.5062 1.0000
0.500 0.6755 0.00625 0.00189 -0.0873 0.4964 1.0000
0.750 0.7031 0.00636 0.00193 -0.0872 0.4868 1.0000
1.000 0.7312 0.00644 0.00197 -0.0871 0.4772 1.0000
1.250 0.7590 0.00655 0.00202 -0.0870 0.4680 1.0000
1.500 0.7870 0.00665 0.00208 -0.0869 0.4586 1.0000
1.750 0.8148 0.00676 0.00215 -0.0868 0.4490 1.0000
2.000 0.8423 0.00690 0.00223 -0.0867 0.4377 1.0000
2.250 0.8700 0.00703 0.00232 -0.0866 0.4251 1.0000
2.500 0.8974 0.00719 0.00241 -0.0864 0.4112 1.0000
2.750 0.9245 0.00737 0.00253 -0.0862 0.3961 1.0000
3.000 0.9513 0.00758 0.00266 -0.0860 0.3805 1.0000
3.250 0.9781 0.00779 0.00280 -0.0858 0.3655 1.0000
3.500 1.0045 0.00804 0.00297 -0.0855 0.3491 1.0000
3.750 1.0306 0.00830 0.00315 -0.0852 0.3328 1.0000
4.000 1.0569 0.00855 0.00333 -0.0849 0.3186 1.0000
4.250 1.0831 0.00880 0.00353 -0.0846 0.3053 1.0000
4.500 1.1092 0.00905 0.00373 -0.0843 0.2930 1.0000
5.000 1.1609 0.00958 0.00414 -0.0837 0.2660 1.0000
5.250 1.1862 0.00990 0.00438 -0.0833 0.2496 1.0000
5.500 1.2111 0.01023 0.00463 -0.0828 0.2323 1.0000
5.750 1.2353 0.01061 0.00492 -0.0823 0.2121 1.0000
6.250 1.2815 0.01154 0.00563 -0.0809 0.1732 1.0000
6.500 1.3048 0.01197 0.00599 -0.0802 0.1604 1.0000
6.750 1.3284 0.01234 0.00632 -0.0795 0.1503 1.0000
7.000 1.3518 0.01273 0.00667 -0.0789 0.1408 1.0000
7.250 1.3744 0.01315 0.00705 -0.0781 0.1315 1.0000
7.500 1.3968 0.01358 0.00743 -0.0773 0.1217 1.0000
7.750 1.4185 0.01403 0.00784 -0.0764 0.1107 1.0000
8.000 1.4373 0.01468 0.00837 -0.0751 0.0910 1.0000
8.250 1.4452 0.01608 0.00947 -0.0723 0.0524 1.0000
8.500 1.4621 0.01677 0.01014 -0.0707 0.0460 1.0000
8.750 1.4777 0.01747 0.01083 -0.0688 0.0418 1.0000
9.000 1.4945 0.01795 0.01135 -0.0671 0.0400 1.0000
9.250 1.5088 0.01857 0.01198 -0.0651 0.0379 1.0000
9.500 1.5203 0.01937 0.01281 -0.0628 0.0357 1.0000
9.750 1.5363 0.01994 0.01342 -0.0612 0.0348 1.0000
10.000 1.5507 0.02061 0.01414 -0.0595 0.0336 1.0000
10.250 1.5633 0.02141 0.01497 -0.0577 0.0323 1.0000
10.500 1.5729 0.02246 0.01605 -0.0556 0.0309 1.0000
10.750 1.5842 0.02342 0.01707 -0.0539 0.0299 1.0000
11.000 1.5971 0.02431 0.01802 -0.0525 0.0292 1.0000
11.250 1.6086 0.02535 0.01910 -0.0510 0.0283 1.0000
11.500 1.6182 0.02655 0.02036 -0.0495 0.0275 1.0000
11.750 1.6251 0.02805 0.02190 -0.0480 0.0266 1.0000
12.000 1.6280 0.02994 0.02386 -0.0464 0.0256 1.0000
12.250 1.6387 0.03123 0.02522 -0.0455 0.0251 1.0000
12.500 1.6473 0.03277 0.02682 -0.0445 0.0244 1.0000
12.750 1.6544 0.03449 0.02861 -0.0436 0.0238 1.0000
13.000 1.6595 0.03647 0.03065 -0.0428 0.0232 1.0000
13.250 1.6619 0.03880 0.03304 -0.0421 0.0226 1.0000
13.500 1.6588 0.04181 0.03613 -0.0415 0.0219 1.0000
13.750 1.6570 0.04478 0.03920 -0.0411 0.0215 1.0000
14.000 1.6606 0.04722 0.04172 -0.0409 0.0211 1.0000
14.250 1.6624 0.04992 0.04451 -0.0408 0.0207 1.0000
14.500 1.6627 0.05282 0.04749 -0.0408 0.0203 1.0000
14.750 1.6620 0.05591 0.05065 -0.0409 0.0198 1.0000
15.000 1.6596 0.05926 0.05408 -0.0411 0.0194 1.0000
15.250 1.6546 0.06299 0.05789 -0.0415 0.0191 1.0000
15.500 1.6459 0.06727 0.06225 -0.0420 0.0187 1.0000
15.750 1.6325 0.07227 0.06735 -0.0429 0.0183 1.0000
16.000 1.6195 0.07733 0.07252 -0.0438 0.0181 1.0000
16.250 1.6145 0.08131 0.07660 -0.0446 0.0179 1.0000
16.500 1.6076 0.08565 0.08103 -0.0455 0.0176 1.0000
16.750 1.5997 0.09022 0.08571 -0.0467 0.0174 1.0000
17.000 1.5907 0.09499 0.09057 -0.0479 0.0172 1.0000
17.250 1.5809 0.09992 0.09560 -0.0494 0.0169 1.0000
17.500 1.5707 0.10500 0.10078 -0.0509 0.0167 1.0000
17.750 1.5605 0.11016 0.10603 -0.0527 0.0165 1.0000
18.000 1.5499 0.11540 0.11136 -0.0545 0.0163 1.0000
18.250 1.5391 0.12073 0.11677 -0.0565 0.0161 1.0000
18.500 1.5277 0.12623 0.12236 -0.0588 0.0159 1.0000
18.750 1.5159 0.13186 0.12808 -0.0612 0.0157 1.0000
19.000 1.5039 0.13762 0.13391 -0.0639 0.0155 1.0000
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