USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 A AIRFOIL (usa35a-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.31 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35a-il-1000000.txt Download as CSV file: xf-usa35a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7011 0.03275 0.02939 -0.1380 0.9356 0.0305
-13.750 -0.7069 0.02984 0.02629 -0.1395 0.9188 0.0305
-13.500 -0.7033 0.02825 0.02456 -0.1387 0.9046 0.0307
-13.250 -0.6915 0.02695 0.02313 -0.1382 0.8921 0.0308
-13.000 -0.6762 0.02589 0.02195 -0.1377 0.8797 0.0310
-12.750 -0.6583 0.02496 0.02092 -0.1373 0.8688 0.0311
-12.250 -0.6194 0.02325 0.01898 -0.1365 0.8484 0.0316
-12.000 -0.5992 0.02241 0.01801 -0.1361 0.8387 0.0318
-11.750 -0.5780 0.02154 0.01702 -0.1357 0.8305 0.0320
-11.500 -0.5562 0.02074 0.01610 -0.1353 0.8218 0.0322
-11.250 -0.5336 0.02001 0.01524 -0.1350 0.8139 0.0324
-11.000 -0.5100 0.01930 0.01443 -0.1347 0.8063 0.0326
-10.750 -0.4862 0.01868 0.01368 -0.1343 0.7980 0.0328
-10.500 -0.4614 0.01809 0.01298 -0.1340 0.7907 0.0330
-10.250 -0.4362 0.01756 0.01235 -0.1338 0.7826 0.0332
-10.000 -0.4107 0.01712 0.01179 -0.1334 0.7741 0.0334
-9.750 -0.3863 0.01631 0.01089 -0.1331 0.7673 0.0337
-9.500 -0.3619 0.01556 0.01006 -0.1328 0.7591 0.0340
-9.250 -0.3359 0.01512 0.00955 -0.1325 0.7511 0.0344
-9.000 -0.3089 0.01475 0.00914 -0.1324 0.7429 0.0347
-8.750 -0.2820 0.01444 0.00877 -0.1322 0.7336 0.0350
-8.500 -0.2545 0.01412 0.00840 -0.1320 0.7250 0.0354
-8.250 -0.2274 0.01383 0.00803 -0.1318 0.7145 0.0358
-8.000 -0.1999 0.01354 0.00767 -0.1317 0.7045 0.0362
-7.750 -0.1727 0.01329 0.00732 -0.1314 0.6922 0.0366
-7.500 -0.1450 0.01305 0.00700 -0.1313 0.6797 0.0370
-7.250 -0.1175 0.01287 0.00671 -0.1310 0.6657 0.0373
-7.000 -0.0914 0.01244 0.00620 -0.1307 0.6508 0.0380
-6.750 -0.0639 0.01222 0.00593 -0.1305 0.6363 0.0386
-6.500 -0.0363 0.01210 0.00574 -0.1303 0.6217 0.0392
-6.250 -0.0089 0.01199 0.00555 -0.1301 0.6071 0.0399
-6.000 0.0191 0.01185 0.00534 -0.1300 0.5949 0.0406
-5.750 0.0469 0.01175 0.00515 -0.1298 0.5837 0.0412
-5.500 0.0746 0.01157 0.00489 -0.1296 0.5734 0.0419
-5.250 0.1021 0.01138 0.00467 -0.1295 0.5643 0.0428
-5.000 0.1306 0.01127 0.00453 -0.1294 0.5569 0.0437
-4.750 0.1585 0.01121 0.00441 -0.1293 0.5491 0.0447
-4.500 0.1872 0.01113 0.00428 -0.1293 0.5435 0.0457
-4.250 0.2156 0.01094 0.00408 -0.1292 0.5385 0.0470
-4.000 0.2440 0.01087 0.00399 -0.1292 0.5333 0.0483
-3.750 0.2723 0.01084 0.00392 -0.1291 0.5280 0.0497
-3.500 0.3010 0.01075 0.00380 -0.1291 0.5245 0.0513
-3.250 0.3301 0.01063 0.00372 -0.1292 0.5219 0.0531
-3.000 0.3591 0.01058 0.00365 -0.1292 0.5187 0.0550
-2.750 0.3877 0.01049 0.00355 -0.1292 0.5152 0.0569
-2.500 0.4161 0.01046 0.00351 -0.1292 0.5114 0.0589
-2.250 0.4443 0.01048 0.00349 -0.1291 0.5070 0.0610
-2.000 0.4731 0.01039 0.00341 -0.1292 0.5043 0.0634
-1.750 0.5023 0.01034 0.00338 -0.1293 0.5021 0.0659
-1.500 0.5313 0.01027 0.00332 -0.1294 0.4996 0.0686
-1.250 0.5601 0.01024 0.00330 -0.1294 0.4967 0.0715
-1.000 0.5887 0.01022 0.00326 -0.1294 0.4936 0.0744
-0.750 0.6168 0.01021 0.00325 -0.1294 0.4900 0.0778
-0.500 0.6445 0.01026 0.00327 -0.1293 0.4856 0.0815
-0.250 0.6737 0.01018 0.00324 -0.1294 0.4836 0.0860
0.000 0.7027 0.01012 0.00322 -0.1295 0.4810 0.0914
0.250 0.7314 0.01008 0.00320 -0.1296 0.4781 0.0982
0.500 0.7597 0.01004 0.00320 -0.1296 0.4749 0.1092
0.750 0.7875 0.00996 0.00322 -0.1296 0.4713 0.1414
1.000 0.8146 0.00990 0.00330 -0.1295 0.4671 0.2056
1.500 0.8716 0.00969 0.00339 -0.1298 0.4616 0.3015
1.750 0.8995 0.00947 0.00348 -0.1300 0.4580 0.4240
2.000 0.9270 0.00939 0.00356 -0.1300 0.4538 0.4977
2.250 0.9527 0.00917 0.00370 -0.1297 0.4485 0.6435
2.500 0.9779 0.00888 0.00383 -0.1291 0.4442 0.8047
2.750 1.0044 0.00864 0.00394 -0.1284 0.4388 0.9919
3.000 1.0329 0.00877 0.00400 -0.1285 0.4328 1.0000
3.250 1.0591 0.00891 0.00409 -0.1282 0.4273 1.0000
3.500 1.0865 0.00901 0.00416 -0.1281 0.4215 1.0000
3.750 1.1120 0.00918 0.00426 -0.1277 0.4136 1.0000
4.000 1.1379 0.00933 0.00437 -0.1273 0.4061 1.0000
4.250 1.1631 0.00951 0.00449 -0.1269 0.3976 1.0000
4.500 1.1876 0.00971 0.00464 -0.1263 0.3895 1.0000
4.750 1.2117 0.00993 0.00480 -0.1257 0.3805 1.0000
5.000 1.2350 0.01017 0.00498 -0.1249 0.3719 1.0000
5.250 1.2575 0.01043 0.00517 -0.1240 0.3630 1.0000
5.500 1.2784 0.01069 0.00539 -0.1228 0.3553 1.0000
5.750 1.2998 0.01095 0.00560 -0.1217 0.3485 1.0000
6.000 1.3195 0.01129 0.00588 -0.1203 0.3415 1.0000
6.250 1.3424 0.01151 0.00610 -0.1196 0.3368 1.0000
6.500 1.3635 0.01181 0.00637 -0.1185 0.3314 1.0000
6.750 1.3832 0.01218 0.00669 -0.1173 0.3258 1.0000
7.000 1.4055 0.01245 0.00696 -0.1165 0.3224 1.0000
7.250 1.4277 0.01272 0.00723 -0.1157 0.3189 1.0000
7.500 1.4485 0.01306 0.00755 -0.1148 0.3151 1.0000
7.750 1.4678 0.01347 0.00794 -0.1136 0.3110 1.0000
8.000 1.4876 0.01386 0.00832 -0.1125 0.3073 1.0000
8.250 1.5098 0.01415 0.00863 -0.1119 0.3046 1.0000
8.500 1.5306 0.01451 0.00899 -0.1110 0.3014 1.0000
8.750 1.5502 0.01493 0.00941 -0.1101 0.2981 1.0000
9.000 1.5679 0.01545 0.00992 -0.1088 0.2945 1.0000
9.250 1.5858 0.01597 0.01043 -0.1077 0.2911 1.0000
9.500 1.6073 0.01631 0.01081 -0.1071 0.2889 1.0000
9.750 1.6271 0.01676 0.01127 -0.1063 0.2861 1.0000
10.000 1.6456 0.01727 0.01180 -0.1053 0.2829 1.0000
10.250 1.6618 0.01792 0.01244 -0.1041 0.2793 1.0000
10.500 1.6764 0.01868 0.01319 -0.1028 0.2755 1.0000
10.750 1.6967 0.01913 0.01368 -0.1022 0.2732 1.0000
11.000 1.7148 0.01971 0.01429 -0.1013 0.2699 1.0000
11.250 1.7309 0.02043 0.01502 -0.1003 0.2660 1.0000
11.500 1.7431 0.02140 0.01598 -0.0989 0.2615 1.0000
11.750 1.7597 0.02211 0.01672 -0.0981 0.2580 1.0000
12.000 1.7753 0.02290 0.01754 -0.0972 0.2538 1.0000
12.250 1.7871 0.02396 0.01859 -0.0959 0.2485 1.0000
12.500 1.7983 0.02509 0.01973 -0.0947 0.2430 1.0000
12.750 1.8100 0.02620 0.02084 -0.0936 0.2363 1.0000
13.000 1.8165 0.02772 0.02235 -0.0921 0.2293 1.0000
13.250 1.8246 0.02917 0.02380 -0.0909 0.2216 1.0000
13.500 1.8287 0.03098 0.02559 -0.0894 0.2135 1.0000
13.750 1.8292 0.03312 0.02770 -0.0878 0.2043 1.0000
14.000 1.8309 0.03523 0.02982 -0.0864 0.1965 1.0000
14.250 1.8279 0.03782 0.03240 -0.0848 0.1893 1.0000
14.500 1.8297 0.04006 0.03466 -0.0837 0.1841 1.0000
14.750 1.8265 0.04279 0.03740 -0.0824 0.1792 1.0000
15.000 1.8270 0.04525 0.03990 -0.0814 0.1754 1.0000
15.250 1.8268 0.04784 0.04253 -0.0806 0.1722 1.0000
15.500 1.8233 0.05080 0.04552 -0.0796 0.1690 1.0000
15.750 1.8167 0.05412 0.04887 -0.0787 0.1656 1.0000
16.000 1.8200 0.05645 0.05126 -0.0782 0.1638 1.0000
16.250 1.8204 0.05913 0.05400 -0.0777 0.1620 1.0000
16.500 1.8202 0.06188 0.05681 -0.0772 0.1602 1.0000
16.750 1.8161 0.06508 0.06006 -0.0767 0.1583 1.0000
17.000 1.8095 0.06858 0.06360 -0.0762 0.1563 1.0000
17.250 1.8017 0.07223 0.06730 -0.0758 0.1540 1.0000
17.500 1.8036 0.07485 0.06998 -0.0756 0.1529 1.0000
17.750 1.8071 0.07724 0.07244 -0.0754 0.1517 1.0000
18.000 1.8058 0.08021 0.07548 -0.0753 0.1503 1.0000
18.250 1.8055 0.08304 0.07836 -0.0751 0.1487 1.0000
18.500 1.8013 0.08639 0.08176 -0.0751 0.1472 1.0000
18.750 1.7972 0.08973 0.08514 -0.0751 0.1455 1.0000
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Polar data table (+)
Polar graphs
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