USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 500,000 Max Cl/Cd: 96.97 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35b-il-500000-n5.txt Download as CSV file: xf-usa35b-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3843 0.10561 0.10307 -0.0304 1.0000 0.0218
-11.250 -0.5699 0.03223 0.02854 -0.0902 0.9664 0.0248
-11.000 -0.5537 0.02855 0.02451 -0.0921 0.9584 0.0250
-10.750 -0.5335 0.02662 0.02237 -0.0926 0.9498 0.0252
-10.500 -0.5105 0.02508 0.02066 -0.0930 0.9422 0.0254
-10.250 -0.4882 0.02380 0.01921 -0.0930 0.9329 0.0256
-10.000 -0.4645 0.02275 0.01801 -0.0929 0.9244 0.0259
-9.750 -0.4408 0.02178 0.01688 -0.0927 0.9150 0.0262
-9.500 -0.4169 0.02075 0.01568 -0.0925 0.9065 0.0265
-9.250 -0.3930 0.01969 0.01442 -0.0922 0.8966 0.0268
-9.000 -0.3686 0.01867 0.01320 -0.0919 0.8868 0.0270
-8.500 -0.3183 0.01696 0.01113 -0.0913 0.8654 0.0275
-8.250 -0.2925 0.01623 0.01023 -0.0910 0.8550 0.0278
-8.000 -0.2665 0.01558 0.00941 -0.0907 0.8439 0.0281
-7.750 -0.2401 0.01499 0.00868 -0.0905 0.8320 0.0283
-7.500 -0.2135 0.01448 0.00803 -0.0902 0.8193 0.0286
-7.250 -0.1869 0.01403 0.00744 -0.0899 0.8054 0.0288
-7.000 -0.1600 0.01364 0.00692 -0.0896 0.7904 0.0290
-6.750 -0.1338 0.01305 0.00623 -0.0893 0.7749 0.0294
-6.250 -0.0800 0.01239 0.00540 -0.0889 0.7400 0.0304
-6.000 -0.0530 0.01212 0.00504 -0.0886 0.7199 0.0308
-5.750 -0.0260 0.01188 0.00468 -0.0884 0.6994 0.0312
-5.500 0.0011 0.01166 0.00436 -0.0881 0.6811 0.0316
-5.250 0.0284 0.01146 0.00407 -0.0879 0.6662 0.0321
-5.000 0.0559 0.01128 0.00379 -0.0878 0.6530 0.0325
-4.500 0.1113 0.01096 0.00333 -0.0875 0.6301 0.0335
-4.250 0.1390 0.01080 0.00311 -0.0874 0.6196 0.0341
-4.000 0.1667 0.01066 0.00290 -0.0873 0.6079 0.0350
-3.750 0.1946 0.01055 0.00275 -0.0872 0.5964 0.0360
-3.500 0.2225 0.01047 0.00262 -0.0871 0.5872 0.0374
-3.250 0.2509 0.01038 0.00250 -0.0871 0.5797 0.0387
-3.000 0.2789 0.01029 0.00238 -0.0871 0.5730 0.0404
-2.750 0.3073 0.01020 0.00229 -0.0870 0.5667 0.0430
-2.500 0.3356 0.01012 0.00221 -0.0870 0.5605 0.0473
-2.000 0.3922 0.00995 0.00212 -0.0870 0.5489 0.0755
-1.750 0.4204 0.00988 0.00209 -0.0870 0.5426 0.0935
-1.500 0.4484 0.00981 0.00208 -0.0870 0.5371 0.1187
-1.250 0.4767 0.00964 0.00209 -0.0871 0.5318 0.1743
-0.750 0.5322 0.00930 0.00213 -0.0871 0.5197 0.3197
-0.500 0.5595 0.00889 0.00221 -0.0872 0.5138 0.4908
-0.250 0.5844 0.00834 0.00231 -0.0867 0.5080 0.7032
0.250 0.6438 0.00788 0.00242 -0.0866 0.4955 1.0000
0.500 0.6713 0.00800 0.00246 -0.0864 0.4881 1.0000
0.750 0.6990 0.00809 0.00251 -0.0863 0.4789 1.0000
1.000 0.7261 0.00823 0.00257 -0.0861 0.4657 1.0000
1.250 0.7530 0.00838 0.00263 -0.0858 0.4494 1.0000
1.500 0.7800 0.00854 0.00271 -0.0856 0.4344 1.0000
1.750 0.8068 0.00872 0.00280 -0.0853 0.4192 1.0000
2.000 0.8336 0.00890 0.00291 -0.0850 0.4041 1.0000
2.500 0.8867 0.00931 0.00317 -0.0845 0.3754 1.0000
2.750 0.9130 0.00954 0.00333 -0.0842 0.3610 1.0000
3.000 0.9392 0.00978 0.00350 -0.0839 0.3474 1.0000
3.250 0.9653 0.01003 0.00369 -0.0835 0.3352 1.0000
3.500 0.9912 0.01029 0.00389 -0.0832 0.3243 1.0000
3.750 1.0175 0.01051 0.00409 -0.0829 0.3144 1.0000
4.000 1.0434 0.01076 0.00430 -0.0825 0.3050 1.0000
4.250 1.0686 0.01106 0.00455 -0.0821 0.2924 1.0000
4.500 1.0935 0.01139 0.00480 -0.0816 0.2765 1.0000
4.750 1.1182 0.01173 0.00506 -0.0811 0.2598 1.0000
5.000 1.1428 0.01207 0.00535 -0.0806 0.2442 1.0000
5.250 1.1668 0.01244 0.00565 -0.0800 0.2268 1.0000
5.500 1.1903 0.01286 0.00598 -0.0794 0.2086 1.0000
5.750 1.2130 0.01333 0.00636 -0.0786 0.1904 1.0000
6.000 1.2354 0.01380 0.00675 -0.0778 0.1753 1.0000
6.250 1.2581 0.01423 0.00714 -0.0771 0.1646 1.0000
6.500 1.2803 0.01468 0.00755 -0.0762 0.1553 1.0000
6.750 1.3024 0.01513 0.00798 -0.0754 0.1461 1.0000
7.000 1.3244 0.01555 0.00839 -0.0745 0.1389 1.0000
7.250 1.3455 0.01602 0.00884 -0.0735 0.1310 1.0000
7.500 1.3668 0.01645 0.00928 -0.0726 0.1245 1.0000
7.750 1.3865 0.01698 0.00978 -0.0714 0.1164 1.0000
8.000 1.4061 0.01748 0.01028 -0.0702 0.1074 1.0000
8.250 1.4228 0.01813 0.01087 -0.0687 0.0936 1.0000
8.500 1.4265 0.01943 0.01191 -0.0653 0.0600 1.0000
8.750 1.4366 0.02036 0.01281 -0.0628 0.0516 1.0000
9.000 1.4481 0.02123 0.01370 -0.0607 0.0470 1.0000
9.250 1.4612 0.02203 0.01454 -0.0588 0.0442 1.0000
9.500 1.4734 0.02291 0.01546 -0.0570 0.0418 1.0000
9.750 1.4838 0.02394 0.01653 -0.0552 0.0397 1.0000
10.000 1.4960 0.02489 0.01754 -0.0536 0.0383 1.0000
10.250 1.5074 0.02593 0.01864 -0.0520 0.0368 1.0000
10.500 1.5172 0.02713 0.01989 -0.0505 0.0354 1.0000
10.750 1.5253 0.02851 0.02133 -0.0490 0.0342 1.0000
11.000 1.5331 0.02998 0.02287 -0.0476 0.0331 1.0000
11.250 1.5424 0.03138 0.02435 -0.0465 0.0322 1.0000
11.500 1.5504 0.03296 0.02600 -0.0454 0.0312 1.0000
11.750 1.5567 0.03474 0.02785 -0.0445 0.0303 1.0000
12.000 1.5614 0.03675 0.02993 -0.0436 0.0294 1.0000
12.250 1.5639 0.03905 0.03231 -0.0428 0.0286 1.0000
12.500 1.5675 0.04134 0.03468 -0.0422 0.0280 1.0000
12.750 1.5716 0.04362 0.03706 -0.0418 0.0273 1.0000
13.000 1.5744 0.04612 0.03966 -0.0415 0.0266 1.0000
13.250 1.5758 0.04882 0.04245 -0.0413 0.0259 1.0000
13.500 1.5756 0.05177 0.04548 -0.0412 0.0252 1.0000
13.750 1.5736 0.05499 0.04878 -0.0413 0.0246 1.0000
14.000 1.5693 0.05858 0.05246 -0.0415 0.0241 1.0000
14.250 1.5669 0.06199 0.05597 -0.0417 0.0236 1.0000
14.500 1.5644 0.06544 0.05954 -0.0421 0.0231 1.0000
14.750 1.5609 0.06909 0.06329 -0.0425 0.0226 1.0000
15.000 1.5565 0.07294 0.06724 -0.0431 0.0221 1.0000
15.250 1.5510 0.07697 0.07138 -0.0439 0.0216 1.0000
15.500 1.5444 0.08123 0.07573 -0.0447 0.0212 1.0000
15.750 1.5366 0.08574 0.08034 -0.0458 0.0207 1.0000
16.000 1.5276 0.09054 0.08522 -0.0470 0.0204 1.0000
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