USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 AIRFOIL (usa35-il) Reynolds number: 200,000 Max Cl/Cd: 66.51 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35-il-200000.txt Download as CSV file: xf-usa35-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 35 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0499 0.10062 0.09679 -0.0950 0.9146 0.0736
-9.500 0.0542 0.09804 0.09419 -0.0955 0.9013 0.0752
-9.250 0.0309 0.09349 0.08962 -0.1016 0.8875 0.0775
-9.000 0.0477 0.09126 0.08732 -0.0994 0.8779 0.0779
-8.750 0.0611 0.08920 0.08526 -0.0982 0.8650 0.0786
-8.500 0.0710 0.08703 0.08304 -0.0978 0.8538 0.0797
-8.250 0.0776 0.08460 0.08057 -0.0982 0.8416 0.0813
-8.000 0.0505 0.07871 0.07465 -0.1071 0.8281 0.0848
-7.750 0.0695 0.07709 0.07296 -0.1043 0.8180 0.0854
-7.500 0.0848 0.07547 0.07132 -0.1030 0.8051 0.0864
-7.250 0.0517 0.06725 0.06295 -0.1204 0.7925 0.0925
-7.000 0.0679 0.06562 0.06135 -0.1171 0.7805 0.0930
-6.750 0.0854 0.06464 0.06033 -0.1138 0.7690 0.0936
-6.500 0.0730 0.05652 0.05176 -0.1282 0.7579 0.1014
-6.250 0.0934 0.05466 0.04999 -0.1263 0.7464 0.1019
-6.000 0.1123 0.05337 0.04868 -0.1246 0.7357 0.1026
-5.750 0.1297 0.05201 0.04731 -0.1237 0.7247 0.1038
-5.500 0.1084 0.03244 0.02585 -0.1337 0.7195 0.0772
-5.250 0.1308 0.03020 0.02330 -0.1337 0.7114 0.0769
-5.000 0.1522 0.02817 0.02105 -0.1333 0.7012 0.0766
-4.750 0.1760 0.02626 0.01871 -0.1330 0.6933 0.0766
-4.500 0.2001 0.02479 0.01685 -0.1325 0.6847 0.0770
-4.250 0.2254 0.02353 0.01541 -0.1323 0.6766 0.0781
-4.000 0.2533 0.02298 0.01481 -0.1324 0.6702 0.0800
-3.750 0.2789 0.02227 0.01397 -0.1320 0.6623 0.0821
-3.500 0.3061 0.02151 0.01288 -0.1316 0.6553 0.0839
-3.250 0.3338 0.02070 0.01187 -0.1315 0.6486 0.0856
-3.000 0.3598 0.02018 0.01139 -0.1311 0.6404 0.0878
-2.750 0.3875 0.01977 0.01081 -0.1309 0.6335 0.0910
-2.500 0.4155 0.01928 0.01019 -0.1308 0.6276 0.0940
-2.250 0.4421 0.01891 0.00986 -0.1305 0.6213 0.0970
-2.000 0.4700 0.01864 0.00947 -0.1303 0.6157 0.1007
-1.750 0.4983 0.01824 0.00907 -0.1303 0.6109 0.1048
-1.500 0.5254 0.01805 0.00887 -0.1301 0.6057 0.1093
-1.250 0.5519 0.01773 0.00862 -0.1298 0.6000 0.1141
-1.000 0.5796 0.01756 0.00843 -0.1296 0.5948 0.1203
-0.750 0.6082 0.01735 0.00821 -0.1297 0.5904 0.1272
-0.500 0.6349 0.01722 0.00815 -0.1294 0.5856 0.1361
-0.250 0.6613 0.01708 0.00810 -0.1291 0.5804 0.1482
0.000 0.6887 0.01691 0.00803 -0.1290 0.5753 0.1697
0.250 0.7167 0.01656 0.00796 -0.1291 0.5706 0.2486
0.500 0.7409 0.01605 0.00816 -0.1288 0.5658 0.4434
0.750 0.7593 0.01543 0.00842 -0.1268 0.5608 0.6888
1.000 0.8034 0.01505 0.00848 -0.1287 0.5553 1.0000
1.250 0.8311 0.01526 0.00849 -0.1287 0.5508 1.0000
1.500 0.8572 0.01554 0.00865 -0.1283 0.5460 1.0000
1.750 0.8811 0.01574 0.00881 -0.1276 0.5403 1.0000
2.000 0.9073 0.01592 0.00888 -0.1272 0.5349 1.0000
2.250 0.9357 0.01615 0.00893 -0.1273 0.5299 1.0000
2.500 0.9604 0.01643 0.00917 -0.1267 0.5245 1.0000
2.750 0.9845 0.01664 0.00936 -0.1261 0.5187 1.0000
3.000 1.0111 0.01684 0.00946 -0.1258 0.5133 1.0000
3.250 1.0406 0.01715 0.00959 -0.1261 0.5084 1.0000
3.500 1.0623 0.01741 0.00990 -0.1250 0.5025 1.0000
3.750 1.0864 0.01762 0.01008 -0.1244 0.4964 1.0000
4.000 1.1137 0.01782 0.01016 -0.1243 0.4910 1.0000
4.250 1.1391 0.01814 0.01042 -0.1239 0.4854 1.0000
4.500 1.1604 0.01838 0.01069 -0.1228 0.4788 1.0000
4.750 1.1858 0.01858 0.01082 -0.1224 0.4732 1.0000
5.000 1.2152 0.01888 0.01096 -0.1228 0.4681 1.0000
5.250 1.2325 0.01914 0.01133 -0.1210 0.4614 1.0000
5.500 1.2554 0.01933 0.01148 -0.1202 0.4552 1.0000
5.750 1.2830 0.01953 0.01152 -0.1202 0.4499 1.0000
6.000 1.2998 0.01982 0.01191 -0.1184 0.4431 1.0000
6.250 1.3208 0.02004 0.01211 -0.1172 0.4370 1.0000
6.500 1.3464 0.02026 0.01221 -0.1170 0.4321 1.0000
6.750 1.3644 0.02062 0.01263 -0.1154 0.4262 1.0000
7.000 1.3823 0.02090 0.01293 -0.1139 0.4201 1.0000
7.250 1.4046 0.02112 0.01305 -0.1131 0.4149 1.0000
7.500 1.4234 0.02151 0.01345 -0.1117 0.4096 1.0000
7.750 1.4381 0.02190 0.01390 -0.1097 0.4043 1.0000
8.000 1.4560 0.02224 0.01421 -0.1082 0.3996 1.0000
8.250 1.4828 0.02256 0.01440 -0.1083 0.3953 1.0000
8.500 1.4914 0.02313 0.01509 -0.1054 0.3904 1.0000
8.750 1.5053 0.02361 0.01562 -0.1034 0.3855 1.0000
9.000 1.5242 0.02402 0.01597 -0.1023 0.3810 1.0000
9.250 1.5462 0.02449 0.01638 -0.1017 0.3767 1.0000
9.500 1.5548 0.02520 0.01721 -0.0992 0.3720 1.0000
9.750 1.5688 0.02581 0.01785 -0.0975 0.3675 1.0000
10.000 1.5887 0.02628 0.01826 -0.0967 0.3633 1.0000
10.250 1.6075 0.02690 0.01886 -0.0958 0.3591 1.0000
10.500 1.6139 0.02781 0.01989 -0.0933 0.3545 1.0000
10.750 1.6261 0.02856 0.02068 -0.0917 0.3499 1.0000
11.000 1.6473 0.02905 0.02108 -0.0911 0.3455 1.0000
11.250 1.6572 0.03000 0.02210 -0.0893 0.3410 1.0000
11.500 1.6615 0.03115 0.02335 -0.0870 0.3361 1.0000
11.750 1.6731 0.03201 0.02423 -0.0855 0.3314 1.0000
12.000 1.6993 0.03239 0.02448 -0.0856 0.3268 1.0000
12.250 1.6933 0.03412 0.02641 -0.0826 0.3222 1.0000
12.500 1.6981 0.03542 0.02778 -0.0807 0.3172 1.0000
12.750 1.7147 0.03614 0.02844 -0.0799 0.3124 1.0000
13.000 1.7196 0.03760 0.02997 -0.0782 0.3075 1.0000
13.250 1.7162 0.03953 0.03204 -0.0761 0.3022 1.0000
13.500 1.7256 0.04070 0.03319 -0.0749 0.2972 1.0000
13.750 1.7345 0.04202 0.03451 -0.0737 0.2920 1.0000
14.000 1.7245 0.04464 0.03729 -0.0716 0.2862 1.0000
14.250 1.7312 0.04609 0.03873 -0.0706 0.2810 1.0000
14.500 1.7361 0.04781 0.04046 -0.0694 0.2757 1.0000
14.750 1.7257 0.05087 0.04368 -0.0679 0.2700 1.0000
15.000 1.7331 0.05242 0.04521 -0.0671 0.2652 1.0000
15.250 1.7387 0.05423 0.04703 -0.0663 0.2605 1.0000
15.500 1.7271 0.05776 0.05072 -0.0653 0.2553 1.0000
15.750 1.7319 0.05971 0.05268 -0.0646 0.2511 1.0000
16.000 1.7552 0.05977 0.05262 -0.0642 0.2474 1.0000
16.250 1.7339 0.06458 0.05768 -0.0634 0.2431 1.0000
16.500 1.7303 0.06759 0.06078 -0.0630 0.2391 1.0000
16.750 1.7391 0.06917 0.06235 -0.0627 0.2357 1.0000
17.000 1.7535 0.07013 0.06326 -0.0622 0.2322 1.0000
17.250 1.7315 0.07543 0.06879 -0.0621 0.2285 1.0000
17.500 1.7263 0.07881 0.07228 -0.0621 0.2249 1.0000
17.750 1.7356 0.08037 0.07382 -0.0620 0.2218 1.0000
18.000 1.7586 0.08020 0.07354 -0.0615 0.2188 1.0000
18.250 1.7296 0.08669 0.08031 -0.0620 0.2158 1.0000
18.500 1.7142 0.09157 0.08535 -0.0625 0.2127 1.0000
18.750 1.7161 0.09417 0.08801 -0.0627 0.2099 1.0000
19.000 1.7333 0.09467 0.08847 -0.0625 0.2075 1.0000
19.250 1.7487 0.09538 0.08915 -0.0623 0.2049 1.0000
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