USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.1 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35b-il-1000000-n5.txt Download as CSV file: xf-usa35b-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4664 0.15126 0.14940 -0.0086 1.0000 0.0131
-15.500 -0.4600 0.14803 0.14617 -0.0100 1.0000 0.0134
-14.000 -0.8629 0.03452 0.03188 -0.0835 0.9996 0.0206
-13.750 -0.8468 0.03088 0.02794 -0.0871 0.9942 0.0208
-13.500 -0.8266 0.02855 0.02538 -0.0890 0.9879 0.0209
-13.250 -0.8035 0.02658 0.02321 -0.0907 0.9828 0.0210
-13.000 -0.7819 0.02485 0.02129 -0.0915 0.9754 0.0211
-12.750 -0.7622 0.02270 0.01891 -0.0922 0.9671 0.0213
-12.500 -0.7393 0.02149 0.01757 -0.0924 0.9583 0.0215
-12.250 -0.7166 0.02058 0.01654 -0.0922 0.9482 0.0216
-12.000 -0.6932 0.01980 0.01566 -0.0919 0.9392 0.0217
-11.750 -0.6694 0.01910 0.01486 -0.0916 0.9303 0.0219
-11.500 -0.6451 0.01844 0.01411 -0.0913 0.9217 0.0220
-11.250 -0.6207 0.01782 0.01337 -0.0910 0.9121 0.0221
-11.000 -0.5957 0.01722 0.01267 -0.0908 0.9030 0.0223
-10.750 -0.5705 0.01667 0.01203 -0.0905 0.8940 0.0225
-10.500 -0.5446 0.01618 0.01144 -0.0903 0.8850 0.0227
-10.250 -0.5189 0.01569 0.01084 -0.0901 0.8755 0.0229
-10.000 -0.4930 0.01515 0.01019 -0.0899 0.8650 0.0231
-9.750 -0.4669 0.01463 0.00955 -0.0897 0.8547 0.0233
-9.500 -0.4407 0.01413 0.00894 -0.0895 0.8438 0.0234
-9.250 -0.4140 0.01367 0.00838 -0.0893 0.8336 0.0236
-9.000 -0.3873 0.01323 0.00783 -0.0891 0.8230 0.0238
-8.750 -0.3605 0.01284 0.00733 -0.0890 0.8108 0.0240
-8.500 -0.3334 0.01247 0.00687 -0.0888 0.7977 0.0241
-8.250 -0.3063 0.01214 0.00643 -0.0887 0.7830 0.0243
-8.000 -0.2791 0.01185 0.00603 -0.0885 0.7670 0.0244
-7.750 -0.2518 0.01158 0.00566 -0.0884 0.7496 0.0246
-7.500 -0.2245 0.01135 0.00532 -0.0882 0.7299 0.0247
-7.000 -0.1704 0.01076 0.00449 -0.0878 0.6860 0.0252
-6.750 -0.1431 0.01053 0.00415 -0.0877 0.6656 0.0255
-6.500 -0.1155 0.01034 0.00389 -0.0876 0.6488 0.0258
-6.250 -0.0876 0.01019 0.00368 -0.0876 0.6361 0.0261
-6.000 -0.0595 0.01005 0.00348 -0.0875 0.6252 0.0265
-5.750 -0.0313 0.00990 0.00328 -0.0875 0.6159 0.0269
-5.250 0.0253 0.00962 0.00290 -0.0875 0.5979 0.0275
-5.000 0.0535 0.00951 0.00273 -0.0875 0.5882 0.0279
-4.750 0.0819 0.00940 0.00258 -0.0875 0.5781 0.0282
-4.500 0.1102 0.00931 0.00243 -0.0875 0.5685 0.0286
-4.250 0.1387 0.00922 0.00230 -0.0875 0.5597 0.0288
-4.000 0.1671 0.00912 0.00216 -0.0875 0.5531 0.0293
-3.750 0.1958 0.00899 0.00202 -0.0875 0.5473 0.0300
-3.500 0.2243 0.00890 0.00192 -0.0875 0.5415 0.0308
-3.250 0.2529 0.00884 0.00184 -0.0876 0.5363 0.0316
-3.000 0.2817 0.00877 0.00176 -0.0876 0.5310 0.0325
-2.750 0.3103 0.00872 0.00170 -0.0877 0.5251 0.0335
-2.500 0.3389 0.00868 0.00164 -0.0877 0.5199 0.0354
-2.250 0.3677 0.00861 0.00159 -0.0877 0.5155 0.0379
-2.000 0.3963 0.00856 0.00155 -0.0878 0.5100 0.0427
-1.750 0.4247 0.00850 0.00153 -0.0878 0.5040 0.0577
-1.500 0.4534 0.00843 0.00152 -0.0879 0.4990 0.0747
-1.250 0.4820 0.00839 0.00151 -0.0879 0.4936 0.0881
-1.000 0.5105 0.00836 0.00151 -0.0879 0.4881 0.1057
-0.750 0.5389 0.00822 0.00153 -0.0880 0.4828 0.1605
-0.500 0.5672 0.00812 0.00156 -0.0881 0.4755 0.2134
-0.250 0.5954 0.00805 0.00159 -0.0882 0.4670 0.2620
0.000 0.6232 0.00784 0.00164 -0.0883 0.4569 0.3780
0.250 0.6506 0.00763 0.00172 -0.0883 0.4433 0.5100
0.500 0.6765 0.00728 0.00183 -0.0881 0.4255 0.7008
0.750 0.6952 0.00687 0.00197 -0.0858 0.4092 0.9195
1.000 0.7305 0.00698 0.00203 -0.0872 0.3887 1.0000
1.250 0.7574 0.00719 0.00213 -0.0870 0.3690 1.0000
1.500 0.7844 0.00739 0.00224 -0.0868 0.3523 1.0000
1.750 0.8114 0.00759 0.00235 -0.0866 0.3385 1.0000
2.000 0.8386 0.00778 0.00247 -0.0864 0.3270 1.0000
2.250 0.8660 0.00793 0.00258 -0.0863 0.3181 1.0000
2.500 0.8931 0.00812 0.00272 -0.0861 0.3089 1.0000
2.750 0.9206 0.00827 0.00284 -0.0860 0.3011 1.0000
3.000 0.9476 0.00847 0.00298 -0.0858 0.2926 1.0000
3.250 0.9749 0.00862 0.00311 -0.0857 0.2848 1.0000
3.500 1.0014 0.00886 0.00328 -0.0854 0.2722 1.0000
3.750 1.0274 0.00913 0.00347 -0.0851 0.2559 1.0000
4.000 1.0532 0.00942 0.00367 -0.0848 0.2387 1.0000
4.250 1.0787 0.00974 0.00389 -0.0844 0.2206 1.0000
4.750 1.1276 0.01054 0.00445 -0.0834 0.1790 1.0000
5.000 1.1521 0.01091 0.00475 -0.0828 0.1640 1.0000
5.250 1.1770 0.01124 0.00502 -0.0824 0.1538 1.0000
5.500 1.2018 0.01156 0.00529 -0.0819 0.1453 1.0000
5.750 1.2270 0.01183 0.00555 -0.0815 0.1390 1.0000
6.000 1.2515 0.01215 0.00584 -0.0810 0.1321 1.0000
6.250 1.2760 0.01246 0.00613 -0.0805 0.1250 1.0000
6.500 1.2996 0.01284 0.00645 -0.0798 0.1168 1.0000
6.750 1.3239 0.01314 0.00675 -0.0793 0.1116 1.0000
7.000 1.3467 0.01354 0.00710 -0.0785 0.1037 1.0000
7.250 1.3691 0.01396 0.00748 -0.0777 0.0931 1.0000
7.750 1.4008 0.01572 0.00893 -0.0743 0.0471 1.0000
8.000 1.4211 0.01620 0.00941 -0.0732 0.0430 1.0000
8.250 1.4403 0.01673 0.00993 -0.0719 0.0395 1.0000
8.500 1.4601 0.01717 0.01040 -0.0707 0.0375 1.0000
8.750 1.4777 0.01766 0.01090 -0.0692 0.0356 1.0000
9.000 1.4931 0.01821 0.01146 -0.0673 0.0337 1.0000
9.250 1.5096 0.01872 0.01200 -0.0656 0.0326 1.0000
9.500 1.5255 0.01927 0.01258 -0.0640 0.0315 1.0000
9.750 1.5403 0.01990 0.01323 -0.0622 0.0303 1.0000
10.000 1.5541 0.02061 0.01396 -0.0605 0.0291 1.0000
10.250 1.5678 0.02135 0.01474 -0.0588 0.0282 1.0000
10.500 1.5822 0.02207 0.01551 -0.0573 0.0275 1.0000
10.750 1.5956 0.02288 0.01636 -0.0558 0.0266 1.0000
11.000 1.6079 0.02379 0.01731 -0.0542 0.0257 1.0000
11.250 1.6191 0.02483 0.01838 -0.0527 0.0248 1.0000
11.500 1.6289 0.02600 0.01960 -0.0512 0.0239 1.0000
11.750 1.6406 0.02708 0.02074 -0.0500 0.0234 1.0000
12.000 1.6511 0.02829 0.02201 -0.0488 0.0228 1.0000
12.250 1.6605 0.02964 0.02340 -0.0476 0.0220 1.0000
12.500 1.6687 0.03114 0.02496 -0.0465 0.0212 1.0000
12.750 1.6753 0.03284 0.02670 -0.0454 0.0205 1.0000
13.000 1.6817 0.03461 0.02854 -0.0445 0.0198 1.0000
13.250 1.6882 0.03644 0.03044 -0.0437 0.0193 1.0000
13.500 1.6934 0.03846 0.03252 -0.0431 0.0187 1.0000
13.750 1.6973 0.04067 0.03480 -0.0425 0.0181 1.0000
14.000 1.6995 0.04311 0.03730 -0.0421 0.0175 1.0000
14.250 1.7005 0.04578 0.04003 -0.0417 0.0169 1.0000
14.500 1.7015 0.04850 0.04284 -0.0415 0.0165 1.0000
14.750 1.7017 0.05137 0.04579 -0.0414 0.0161 1.0000
15.000 1.7007 0.05444 0.04894 -0.0415 0.0156 1.0000
15.250 1.6984 0.05772 0.05230 -0.0416 0.0151 1.0000
15.500 1.6947 0.06122 0.05587 -0.0418 0.0147 1.0000
15.750 1.6893 0.06496 0.05970 -0.0422 0.0143 1.0000
16.000 1.6827 0.06894 0.06376 -0.0427 0.0139 1.0000
16.250 1.6766 0.07293 0.06784 -0.0433 0.0136 1.0000
16.500 1.6697 0.07707 0.07208 -0.0440 0.0134 1.0000
16.750 1.6617 0.08142 0.07653 -0.0448 0.0131 1.0000
17.000 1.6528 0.08598 0.08118 -0.0458 0.0129 1.0000
17.250 1.6431 0.09074 0.08604 -0.0470 0.0126 1.0000
17.500 1.6324 0.09569 0.09109 -0.0483 0.0124 1.0000
17.750 1.6210 0.10082 0.09631 -0.0498 0.0122 1.0000
18.000 1.6090 0.10613 0.10172 -0.0515 0.0120 1.0000
18.250 1.5965 0.11160 0.10729 -0.0534 0.0118 1.0000
18.500 1.5833 0.11721 0.11300 -0.0554 0.0116 1.0000
18.750 1.5698 0.12296 0.11884 -0.0577 0.0114 1.0000
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Polar data table (+)
Polar graphs
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