USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 A AIRFOIL (usa35a-il) Reynolds number: 200,000 Max Cl/Cd: 66.54 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35a-il-200000.txt Download as CSV file: xf-usa35a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 35 A 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
------ -------- --------- --------- -------- -------- --------
-9.250 0.0583 0.09521 0.09134 -0.0961 0.8894 0.0757
-9.000 0.0648 0.09282 0.08890 -0.0961 0.8782 0.0773
-8.750 0.0366 0.08779 0.08385 -0.1040 0.8635 0.0805
-8.500 0.0547 0.08570 0.08172 -0.1015 0.8531 0.0810
-8.250 0.0690 0.08372 0.07969 -0.1001 0.8412 0.0816
-8.000 0.0801 0.08163 0.07757 -0.0997 0.8293 0.0827
-7.750 0.0875 0.07925 0.07511 -0.1001 0.8179 0.0843
-7.500 0.0535 0.07238 0.06824 -0.1118 0.8036 0.0882
-7.250 0.0741 0.07095 0.06673 -0.1084 0.7935 0.0888
-7.000 0.0886 0.06932 0.06509 -0.1071 0.7806 0.0896
-6.750 0.0655 0.05955 0.05500 -0.1260 0.7697 0.0965
-6.500 0.0850 0.05821 0.05371 -0.1234 0.7577 0.0969
-6.250 0.1026 0.05708 0.05257 -0.1213 0.7463 0.0976
-6.000 0.1194 0.05580 0.05123 -0.1201 0.7351 0.0990
-5.750 0.1233 0.04941 0.04451 -0.1282 0.7254 0.1065
-5.500 0.1059 0.03073 0.02400 -0.1340 0.7198 0.0738
-5.250 0.1281 0.02848 0.02127 -0.1337 0.7116 0.0733
-5.000 0.1501 0.02664 0.01915 -0.1333 0.7017 0.0738
-4.750 0.1767 0.02609 0.01871 -0.1332 0.6931 0.0753
-4.500 0.2018 0.02512 0.01754 -0.1330 0.6848 0.0769
-4.250 0.2269 0.02387 0.01598 -0.1326 0.6764 0.0782
-4.000 0.2541 0.02274 0.01443 -0.1324 0.6700 0.0794
-3.750 0.2799 0.02180 0.01324 -0.1320 0.6626 0.0809
-3.500 0.3067 0.02117 0.01263 -0.1319 0.6552 0.0829
-3.000 0.3611 0.02014 0.01122 -0.1313 0.6406 0.0885
-2.750 0.3881 0.01959 0.01067 -0.1311 0.6334 0.0912
-2.500 0.4171 0.01925 0.01015 -0.1310 0.6276 0.0946
-2.250 0.4432 0.01880 0.00972 -0.1307 0.6214 0.0982
-2.000 0.4706 0.01850 0.00943 -0.1305 0.6156 0.1025
-1.750 0.4988 0.01815 0.00898 -0.1304 0.6106 0.1068
-1.500 0.5268 0.01794 0.00879 -0.1304 0.6058 0.1122
-1.250 0.5530 0.01766 0.00855 -0.1300 0.6002 0.1177
-1.000 0.5802 0.01746 0.00838 -0.1298 0.5948 0.1245
-0.750 0.6083 0.01724 0.00816 -0.1298 0.5901 0.1322
-0.500 0.6363 0.01714 0.00808 -0.1297 0.5855 0.1422
-0.250 0.6623 0.01702 0.00808 -0.1294 0.5804 0.1556
0.000 0.6894 0.01688 0.00806 -0.1292 0.5753 0.1797
0.250 0.7169 0.01653 0.00799 -0.1292 0.5706 0.2543
0.500 0.7430 0.01605 0.00815 -0.1292 0.5660 0.4555
0.750 0.7607 0.01545 0.00842 -0.1271 0.5609 0.6881
1.000 0.8028 0.01506 0.00850 -0.1287 0.5552 0.9970
1.250 0.8308 0.01525 0.00851 -0.1286 0.5504 1.0000
1.500 0.8593 0.01555 0.00862 -0.1287 0.5458 1.0000
1.750 0.8824 0.01575 0.00881 -0.1279 0.5405 1.0000
2.000 0.9078 0.01594 0.00892 -0.1274 0.5350 1.0000
2.250 0.9353 0.01614 0.00897 -0.1273 0.5298 1.0000
2.500 0.9632 0.01645 0.00914 -0.1273 0.5247 1.0000
2.750 0.9857 0.01666 0.00937 -0.1263 0.5187 1.0000
3.000 1.0114 0.01686 0.00949 -0.1259 0.5130 1.0000
3.250 1.0396 0.01709 0.00958 -0.1260 0.5080 1.0000
3.500 1.0646 0.01741 0.00986 -0.1255 0.5026 1.0000
3.750 1.0874 0.01764 0.01010 -0.1246 0.4964 1.0000
4.000 1.1135 0.01784 0.01022 -0.1243 0.4908 1.0000
4.250 1.1434 0.01816 0.01037 -0.1247 0.4856 1.0000
4.500 1.1622 0.01840 0.01070 -0.1232 0.4791 1.0000
4.750 1.1860 0.01861 0.01087 -0.1225 0.4730 1.0000
5.000 1.2134 0.01882 0.01096 -0.1225 0.4678 1.0000
5.250 1.2348 0.01914 0.01130 -0.1214 0.4616 1.0000
5.500 1.2559 0.01935 0.01152 -0.1203 0.4551 1.0000
5.750 1.2811 0.01952 0.01158 -0.1199 0.4495 1.0000
6.000 1.3028 0.01982 0.01187 -0.1189 0.4435 1.0000
6.250 1.3217 0.02007 0.01215 -0.1175 0.4370 1.0000
6.500 1.3447 0.02027 0.01228 -0.1167 0.4316 1.0000
6.750 1.3679 0.02060 0.01255 -0.1161 0.4264 1.0000
7.000 1.3837 0.02093 0.01295 -0.1142 0.4202 1.0000
7.250 1.4035 0.02117 0.01316 -0.1130 0.4147 1.0000
7.500 1.4280 0.02146 0.01334 -0.1125 0.4097 1.0000
7.750 1.4399 0.02190 0.01388 -0.1101 0.4042 1.0000
8.000 1.4559 0.02227 0.01426 -0.1083 0.3994 1.0000
8.250 1.4774 0.02260 0.01452 -0.1074 0.3951 1.0000
8.500 1.4961 0.02308 0.01499 -0.1062 0.3906 1.0000
8.750 1.5075 0.02363 0.01563 -0.1039 0.3857 1.0000
9.000 1.5233 0.02410 0.01610 -0.1023 0.3810 1.0000
9.250 1.5468 0.02447 0.01637 -0.1019 0.3767 1.0000
9.500 1.5589 0.02515 0.01711 -0.0999 0.3722 1.0000
9.750 1.5697 0.02583 0.01787 -0.0978 0.3674 1.0000
10.000 1.5854 0.02640 0.01844 -0.0964 0.3630 1.0000
10.250 1.6124 0.02678 0.01869 -0.0965 0.3587 1.0000
10.500 1.6174 0.02774 0.01979 -0.0939 0.3545 1.0000
10.750 1.6267 0.02860 0.02073 -0.0919 0.3499 1.0000
11.000 1.6414 0.02929 0.02141 -0.0906 0.3455 1.0000
11.250 1.6673 0.02972 0.02172 -0.0906 0.3410 1.0000
11.500 1.6657 0.03106 0.02324 -0.0876 0.3364 1.0000
11.750 1.6728 0.03212 0.02437 -0.0857 0.3316 1.0000
12.000 1.6897 0.03278 0.02498 -0.0848 0.3269 1.0000
12.250 1.7002 0.03385 0.02608 -0.0833 0.3221 1.0000
12.500 1.6989 0.03546 0.02783 -0.0809 0.3171 1.0000
12.750 1.7077 0.03658 0.02896 -0.0795 0.3122 1.0000
13.000 1.7300 0.03709 0.02936 -0.0792 0.3073 1.0000
13.250 1.7186 0.03946 0.03195 -0.0764 0.3022 1.0000
13.500 1.7214 0.04106 0.03360 -0.0748 0.2969 1.0000
13.750 1.7451 0.04138 0.03377 -0.0745 0.2918 1.0000
14.000 1.7283 0.04445 0.03708 -0.0720 0.2864 1.0000
14.250 1.7275 0.04650 0.03920 -0.0706 0.2809 1.0000
14.500 1.7488 0.04689 0.03944 -0.0701 0.2759 1.0000
14.750 1.7296 0.05063 0.04342 -0.0682 0.2703 1.0000
15.000 1.7285 0.05298 0.04582 -0.0672 0.2650 1.0000
15.250 1.7485 0.05339 0.04610 -0.0667 0.2605 1.0000
15.500 1.7311 0.05745 0.05039 -0.0655 0.2555 1.0000
15.750 1.7284 0.06019 0.05321 -0.0648 0.2508 1.0000
16.000 1.7405 0.06139 0.05436 -0.0643 0.2471 1.0000
16.250 1.7453 0.06343 0.05644 -0.0637 0.2433 1.0000
16.500 1.7314 0.06757 0.06076 -0.0632 0.2392 1.0000
16.750 1.7328 0.07004 0.06330 -0.0628 0.2355 1.0000
17.000 1.7471 0.07099 0.06418 -0.0625 0.2323 1.0000
17.250 1.7469 0.07368 0.06695 -0.0622 0.2288 1.0000
17.500 1.7280 0.07873 0.07220 -0.0622 0.2251 1.0000
17.750 1.7267 0.08164 0.07517 -0.0623 0.2216 1.0000
18.000 1.7398 0.08271 0.07620 -0.0621 0.2186 1.0000
18.250 1.7508 0.08405 0.07753 -0.0618 0.2158 1.0000
18.500 1.7226 0.09056 0.08430 -0.0625 0.2128 1.0000
18.750 1.7090 0.09526 0.08914 -0.0631 0.2099 1.0000
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