USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 35 AIRFOIL (usa35-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.47 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35-il-1000000-n5.txt Download as CSV file: xf-usa35-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8659 0.03494 0.03127 -0.1314 0.9185 0.0261
-15.250 -0.8807 0.02924 0.02527 -0.1381 0.8969 0.0261
-15.000 -0.8803 0.02732 0.02317 -0.1378 0.8774 0.0262
-14.750 -0.8712 0.02600 0.02169 -0.1371 0.8606 0.0263
-14.500 -0.8570 0.02488 0.02043 -0.1367 0.8468 0.0264
-14.250 -0.8405 0.02390 0.01931 -0.1362 0.8345 0.0265
-14.000 -0.8221 0.02301 0.01831 -0.1358 0.8244 0.0267
-13.750 -0.8024 0.02220 0.01740 -0.1354 0.8157 0.0268
-13.500 -0.7814 0.02145 0.01655 -0.1350 0.8073 0.0269
-13.250 -0.7598 0.02077 0.01576 -0.1346 0.7983 0.0271
-13.000 -0.7373 0.02012 0.01501 -0.1342 0.7907 0.0272
-12.750 -0.7141 0.01951 0.01432 -0.1339 0.7823 0.0273
-12.250 -0.6660 0.01841 0.01305 -0.1332 0.7682 0.0276
-12.000 -0.6412 0.01792 0.01247 -0.1329 0.7605 0.0277
-11.750 -0.6162 0.01747 0.01192 -0.1326 0.7528 0.0278
-11.500 -0.5905 0.01702 0.01140 -0.1324 0.7461 0.0279
-11.250 -0.5654 0.01650 0.01082 -0.1321 0.7379 0.0282
-11.000 -0.5401 0.01604 0.01028 -0.1318 0.7300 0.0284
-10.750 -0.5138 0.01563 0.00982 -0.1316 0.7220 0.0287
-10.500 -0.4874 0.01529 0.00941 -0.1314 0.7124 0.0290
-10.250 -0.4606 0.01496 0.00902 -0.1312 0.7031 0.0292
-10.000 -0.4340 0.01466 0.00865 -0.1309 0.6914 0.0294
-9.750 -0.4069 0.01437 0.00829 -0.1307 0.6803 0.0297
-9.500 -0.3800 0.01412 0.00795 -0.1305 0.6681 0.0300
-9.250 -0.3526 0.01385 0.00762 -0.1303 0.6560 0.0302
-9.000 -0.3255 0.01362 0.00730 -0.1301 0.6434 0.0305
-8.750 -0.2983 0.01342 0.00700 -0.1299 0.6291 0.0308
-8.500 -0.2707 0.01321 0.00672 -0.1297 0.6154 0.0310
-8.250 -0.2433 0.01303 0.00645 -0.1295 0.6022 0.0313
-7.750 -0.1882 0.01263 0.00591 -0.1292 0.5784 0.0320
-7.250 -0.1324 0.01230 0.00547 -0.1289 0.5596 0.0328
-7.000 -0.1044 0.01215 0.00528 -0.1288 0.5512 0.0333
-6.750 -0.0761 0.01202 0.00510 -0.1287 0.5444 0.0338
-6.500 -0.0475 0.01187 0.00491 -0.1287 0.5395 0.0343
-6.250 -0.0189 0.01174 0.00474 -0.1286 0.5346 0.0348
-6.000 0.0095 0.01162 0.00458 -0.1286 0.5296 0.0352
-5.750 0.0379 0.01148 0.00442 -0.1285 0.5245 0.0359
-5.500 0.0667 0.01135 0.00428 -0.1285 0.5204 0.0367
-5.250 0.0954 0.01126 0.00416 -0.1285 0.5151 0.0375
-5.000 0.1239 0.01118 0.00404 -0.1285 0.5098 0.0384
-4.500 0.1813 0.01100 0.00382 -0.1284 0.5016 0.0401
-4.250 0.2103 0.01091 0.00372 -0.1285 0.4978 0.0412
-4.000 0.2392 0.01084 0.00364 -0.1285 0.4937 0.0422
-3.750 0.2679 0.01079 0.00355 -0.1285 0.4900 0.0432
-3.500 0.2964 0.01072 0.00348 -0.1285 0.4863 0.0444
-3.250 0.3252 0.01067 0.00342 -0.1285 0.4834 0.0457
-3.000 0.3544 0.01061 0.00336 -0.1286 0.4817 0.0471
-2.750 0.3835 0.01054 0.00330 -0.1286 0.4795 0.0484
-2.500 0.4125 0.01048 0.00325 -0.1287 0.4767 0.0501
-2.250 0.4414 0.01045 0.00321 -0.1287 0.4735 0.0517
-2.000 0.4701 0.01042 0.00317 -0.1287 0.4701 0.0531
-1.750 0.4985 0.01040 0.00314 -0.1287 0.4668 0.0547
-1.500 0.5270 0.01040 0.00312 -0.1287 0.4637 0.0564
-1.250 0.5561 0.01036 0.00310 -0.1288 0.4618 0.0582
-1.000 0.5850 0.01032 0.00308 -0.1289 0.4593 0.0604
-0.750 0.6138 0.01030 0.00307 -0.1289 0.4564 0.0625
-0.500 0.6423 0.01029 0.00306 -0.1289 0.4528 0.0649
-0.250 0.6705 0.01031 0.00307 -0.1289 0.4488 0.0677
0.000 0.6984 0.01033 0.00308 -0.1288 0.4446 0.0708
0.250 0.7271 0.01032 0.00309 -0.1289 0.4416 0.0744
0.500 0.7556 0.01031 0.00310 -0.1289 0.4380 0.0785
0.750 0.7837 0.01032 0.00312 -0.1289 0.4336 0.0837
1.250 0.8390 0.01037 0.00320 -0.1287 0.4248 0.1026
1.500 0.8670 0.01032 0.00324 -0.1287 0.4201 0.1314
1.750 0.8943 0.01029 0.00331 -0.1287 0.4140 0.1753
2.000 0.9210 0.01034 0.00340 -0.1285 0.4071 0.2059
2.250 0.9476 0.01038 0.00349 -0.1283 0.3975 0.2379
2.500 0.9733 0.01046 0.00360 -0.1279 0.3868 0.2761
2.750 0.9982 0.01054 0.00376 -0.1275 0.3750 0.3338
3.000 1.0239 0.01049 0.00393 -0.1273 0.3660 0.4405
3.250 1.0486 0.01048 0.00413 -0.1269 0.3575 0.5483
3.500 1.0735 0.01035 0.00434 -0.1265 0.3496 0.6964
3.750 1.0899 0.01014 0.00463 -0.1241 0.3412 0.9024
4.000 1.1176 0.01023 0.00477 -0.1240 0.3345 1.0000
4.250 1.1415 0.01046 0.00494 -0.1233 0.3283 1.0000
4.500 1.1652 0.01069 0.00513 -0.1226 0.3233 1.0000
4.750 1.1892 0.01087 0.00528 -0.1219 0.3197 1.0000
5.000 1.2118 0.01107 0.00546 -0.1210 0.3156 1.0000
5.250 1.2333 0.01134 0.00568 -0.1199 0.3107 1.0000
5.500 1.2550 0.01161 0.00591 -0.1189 0.3057 1.0000
5.750 1.2780 0.01183 0.00612 -0.1181 0.3022 1.0000
6.000 1.3004 0.01208 0.00635 -0.1173 0.2985 1.0000
6.250 1.3223 0.01236 0.00661 -0.1164 0.2949 1.0000
6.500 1.3432 0.01269 0.00691 -0.1154 0.2909 1.0000
6.750 1.3657 0.01295 0.00717 -0.1146 0.2881 1.0000
7.000 1.3882 0.01322 0.00744 -0.1139 0.2851 1.0000
7.250 1.4098 0.01353 0.00774 -0.1131 0.2821 1.0000
7.500 1.4309 0.01387 0.00807 -0.1122 0.2791 1.0000
7.750 1.4509 0.01426 0.00844 -0.1112 0.2758 1.0000
8.000 1.4713 0.01464 0.00882 -0.1103 0.2730 1.0000
8.250 1.4930 0.01497 0.00916 -0.1095 0.2706 1.0000
8.500 1.5135 0.01536 0.00955 -0.1087 0.2673 1.0000
8.750 1.5326 0.01582 0.01000 -0.1077 0.2635 1.0000
9.000 1.5506 0.01635 0.01052 -0.1066 0.2596 1.0000
9.250 1.5695 0.01684 0.01101 -0.1056 0.2567 1.0000
9.500 1.5891 0.01730 0.01149 -0.1048 0.2537 1.0000
9.750 1.6072 0.01786 0.01205 -0.1038 0.2498 1.0000
10.000 1.6232 0.01854 0.01272 -0.1026 0.2455 1.0000
10.250 1.6397 0.01921 0.01339 -0.1016 0.2417 1.0000
10.500 1.6567 0.01987 0.01407 -0.1006 0.2374 1.0000
10.750 1.6711 0.02070 0.01489 -0.0994 0.2320 1.0000
11.000 1.6846 0.02161 0.01579 -0.0982 0.2270 1.0000
11.250 1.6979 0.02255 0.01673 -0.0970 0.2207 1.0000
11.500 1.7079 0.02373 0.01790 -0.0955 0.2138 1.0000
11.750 1.7169 0.02502 0.01917 -0.0941 0.2055 1.0000
12.000 1.7237 0.02651 0.02063 -0.0925 0.1972 1.0000
12.250 1.7272 0.02826 0.02235 -0.0907 0.1882 1.0000
12.500 1.7307 0.03010 0.02418 -0.0891 0.1803 1.0000
12.750 1.7348 0.03196 0.02604 -0.0877 0.1746 1.0000
13.000 1.7403 0.03374 0.02782 -0.0865 0.1698 1.0000
13.250 1.7430 0.03581 0.02991 -0.0852 0.1656 1.0000
13.500 1.7490 0.03766 0.03179 -0.0842 0.1627 1.0000
13.750 1.7554 0.03949 0.03366 -0.0833 0.1602 1.0000
14.000 1.7594 0.04160 0.03580 -0.0824 0.1578 1.0000
14.250 1.7611 0.04395 0.03818 -0.0814 0.1553 1.0000
14.500 1.7634 0.04628 0.04056 -0.0806 0.1529 1.0000
14.750 1.7688 0.04837 0.04270 -0.0800 0.1514 1.0000
15.000 1.7728 0.05063 0.04501 -0.0794 0.1500 1.0000
15.250 1.7763 0.05293 0.04737 -0.0788 0.1484 1.0000
15.500 1.7767 0.05560 0.05008 -0.0782 0.1467 1.0000
15.750 1.7761 0.05841 0.05294 -0.0776 0.1451 1.0000
16.000 1.7749 0.06129 0.05587 -0.0771 0.1432 1.0000
16.250 1.7731 0.06430 0.05894 -0.0767 0.1415 1.0000
16.500 1.7764 0.06670 0.06140 -0.0764 0.1403 1.0000
16.750 1.7773 0.06943 0.06419 -0.0761 0.1391 1.0000
17.000 1.7784 0.07211 0.06693 -0.0758 0.1377 1.0000
17.250 1.7769 0.07513 0.07001 -0.0756 0.1363 1.0000
17.500 1.7759 0.07809 0.07302 -0.0754 0.1348 1.0000
17.750 1.7719 0.08141 0.07640 -0.0752 0.1334 1.0000
18.000 1.7696 0.08452 0.07955 -0.0751 0.1320 1.0000
18.250 1.7663 0.08783 0.08292 -0.0751 0.1308 1.0000
18.500 1.7694 0.09033 0.08549 -0.0752 0.1297 1.0000
18.750 1.7686 0.09333 0.08855 -0.0753 0.1282 1.0000
19.000 1.7681 0.09628 0.09155 -0.0754 0.1267 1.0000
19.250 1.7675 0.09922 0.09454 -0.0756 0.1252 1.0000
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