USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 35 A AIRFOIL (usa35a-il) Reynolds number: 500,000 Max Cl/Cd: 92.3 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35a-il-500000-n5.txt Download as CSV file: xf-usa35a-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6048 0.03428 0.02991 -0.1346 0.8594 0.0300
-12.750 -0.6124 0.03118 0.02653 -0.1359 0.8454 0.0302
-12.500 -0.6057 0.02916 0.02427 -0.1361 0.8348 0.0304
-12.250 -0.5938 0.02754 0.02244 -0.1360 0.8249 0.0306
-11.750 -0.5611 0.02502 0.01952 -0.1354 0.8077 0.0309
-11.500 -0.5424 0.02397 0.01834 -0.1350 0.7988 0.0311
-11.250 -0.5220 0.02310 0.01736 -0.1346 0.7908 0.0313
-11.000 -0.5001 0.02232 0.01651 -0.1343 0.7820 0.0315
-10.750 -0.4775 0.02165 0.01573 -0.1339 0.7734 0.0317
-10.500 -0.4539 0.02101 0.01500 -0.1337 0.7658 0.0319
-10.250 -0.4299 0.02041 0.01431 -0.1334 0.7573 0.0321
-10.000 -0.4057 0.01985 0.01364 -0.1330 0.7493 0.0324
-9.750 -0.3808 0.01929 0.01300 -0.1328 0.7409 0.0326
-9.500 -0.3559 0.01877 0.01237 -0.1324 0.7317 0.0329
-9.250 -0.3306 0.01826 0.01176 -0.1322 0.7231 0.0333
-9.000 -0.3051 0.01778 0.01117 -0.1319 0.7131 0.0336
-8.750 -0.2794 0.01733 0.01060 -0.1316 0.7036 0.0340
-8.500 -0.2534 0.01690 0.01005 -0.1313 0.6923 0.0343
-8.250 -0.2274 0.01651 0.00954 -0.1310 0.6809 0.0346
-8.000 -0.2016 0.01612 0.00907 -0.1306 0.6679 0.0350
-7.750 -0.1752 0.01580 0.00869 -0.1304 0.6555 0.0354
-7.500 -0.1488 0.01554 0.00834 -0.1301 0.6433 0.0358
-7.250 -0.1219 0.01528 0.00800 -0.1298 0.6306 0.0362
-7.000 -0.0952 0.01505 0.00768 -0.1295 0.6191 0.0368
-6.750 -0.0683 0.01483 0.00736 -0.1293 0.6073 0.0374
-6.500 -0.0412 0.01461 0.00705 -0.1290 0.5973 0.0381
-6.250 -0.0142 0.01440 0.00675 -0.1288 0.5875 0.0387
-6.000 0.0130 0.01420 0.00651 -0.1286 0.5792 0.0394
-5.750 0.0405 0.01404 0.00630 -0.1284 0.5708 0.0401
-5.500 0.0676 0.01390 0.00609 -0.1281 0.5634 0.0409
-5.250 0.0956 0.01372 0.00586 -0.1280 0.5578 0.0418
-5.000 0.1235 0.01356 0.00564 -0.1279 0.5524 0.0427
-4.750 0.1510 0.01341 0.00547 -0.1277 0.5468 0.0436
-4.500 0.1786 0.01332 0.00533 -0.1276 0.5408 0.0446
-4.250 0.2068 0.01319 0.00517 -0.1275 0.5351 0.0459
-4.000 0.2346 0.01310 0.00502 -0.1273 0.5292 0.0472
-3.750 0.2621 0.01302 0.00491 -0.1271 0.5236 0.0486
-3.500 0.2901 0.01295 0.00482 -0.1270 0.5187 0.0502
-3.250 0.3185 0.01286 0.00470 -0.1270 0.5144 0.0520
-3.000 0.3466 0.01277 0.00461 -0.1269 0.5107 0.0536
-2.750 0.3747 0.01271 0.00453 -0.1268 0.5074 0.0555
-2.500 0.4027 0.01266 0.00445 -0.1267 0.5039 0.0573
-2.250 0.4303 0.01263 0.00440 -0.1266 0.5002 0.0593
-2.000 0.4589 0.01257 0.00434 -0.1266 0.4974 0.0617
-1.750 0.4873 0.01250 0.00429 -0.1266 0.4943 0.0640
-1.500 0.5156 0.01246 0.00426 -0.1265 0.4912 0.0666
-1.250 0.5437 0.01243 0.00422 -0.1265 0.4880 0.0691
-1.000 0.5716 0.01241 0.00420 -0.1264 0.4848 0.0722
-0.750 0.5992 0.01242 0.00418 -0.1262 0.4815 0.0753
-0.500 0.6269 0.01241 0.00418 -0.1261 0.4783 0.0790
-0.250 0.6552 0.01237 0.00417 -0.1261 0.4752 0.0830
0.000 0.6833 0.01235 0.00416 -0.1261 0.4717 0.0877
0.250 0.7111 0.01233 0.00417 -0.1260 0.4681 0.0931
0.500 0.7385 0.01234 0.00418 -0.1258 0.4645 0.1001
0.750 0.7655 0.01235 0.00420 -0.1256 0.4609 0.1106
1.000 0.7929 0.01231 0.00425 -0.1255 0.4577 0.1331
1.250 0.8206 0.01221 0.00432 -0.1256 0.4543 0.1851
1.500 0.8479 0.01219 0.00439 -0.1255 0.4502 0.2163
1.750 0.8747 0.01219 0.00445 -0.1253 0.4456 0.2466
2.000 0.9005 0.01218 0.00455 -0.1250 0.4409 0.2972
2.250 0.9275 0.01201 0.00468 -0.1250 0.4365 0.4071
2.500 0.9540 0.01191 0.00481 -0.1248 0.4314 0.4956
2.750 0.9780 0.01157 0.00501 -0.1243 0.4261 0.6884
3.000 0.9988 0.01140 0.00518 -0.1227 0.4212 0.8222
3.250 1.0269 0.01129 0.00529 -0.1224 0.4147 1.0000
3.500 1.0509 0.01148 0.00541 -0.1217 0.4070 1.0000
3.750 1.0751 0.01167 0.00554 -0.1210 0.3993 1.0000
4.000 1.0980 0.01190 0.00570 -0.1201 0.3903 1.0000
4.250 1.1205 0.01214 0.00587 -0.1192 0.3819 1.0000
4.500 1.1406 0.01241 0.00607 -0.1179 0.3729 1.0000
4.750 1.1611 0.01268 0.00629 -0.1166 0.3653 1.0000
5.000 1.1816 0.01298 0.00653 -0.1154 0.3578 1.0000
5.250 1.2015 0.01332 0.00681 -0.1141 0.3518 1.0000
5.500 1.2231 0.01361 0.00707 -0.1131 0.3457 1.0000
5.750 1.2427 0.01399 0.00740 -0.1119 0.3394 1.0000
6.000 1.2626 0.01436 0.00774 -0.1107 0.3342 1.0000
6.250 1.2840 0.01469 0.00805 -0.1098 0.3296 1.0000
6.500 1.3038 0.01509 0.00843 -0.1087 0.3246 1.0000
6.750 1.3218 0.01558 0.00886 -0.1074 0.3194 1.0000
7.000 1.3424 0.01596 0.00924 -0.1064 0.3152 1.0000
7.250 1.3626 0.01636 0.00965 -0.1055 0.3114 1.0000
7.500 1.3816 0.01683 0.01010 -0.1044 0.3075 1.0000
7.750 1.3992 0.01738 0.01063 -0.1032 0.3037 1.0000
8.000 1.4177 0.01789 0.01114 -0.1022 0.3006 1.0000
8.250 1.4377 0.01835 0.01161 -0.1013 0.2976 1.0000
8.500 1.4565 0.01887 0.01214 -0.1004 0.2941 1.0000
8.750 1.4739 0.01947 0.01275 -0.0993 0.2905 1.0000
9.000 1.4897 0.02018 0.01345 -0.0981 0.2870 1.0000
9.250 1.5060 0.02087 0.01415 -0.0970 0.2841 1.0000
9.500 1.5246 0.02145 0.01476 -0.0962 0.2814 1.0000
9.750 1.5422 0.02210 0.01544 -0.0953 0.2782 1.0000
10.000 1.5578 0.02288 0.01624 -0.0943 0.2748 1.0000
10.250 1.5718 0.02377 0.01713 -0.0931 0.2713 1.0000
10.500 1.5849 0.02475 0.01812 -0.0920 0.2680 1.0000
10.750 1.6017 0.02550 0.01892 -0.0912 0.2650 1.0000
11.000 1.6162 0.02643 0.01988 -0.0902 0.2612 1.0000
11.250 1.6283 0.02753 0.02099 -0.0891 0.2569 1.0000
11.500 1.6373 0.02888 0.02234 -0.0879 0.2529 1.0000
11.750 1.6516 0.02986 0.02338 -0.0870 0.2487 1.0000
12.000 1.6620 0.03118 0.02472 -0.0860 0.2436 1.0000
12.250 1.6688 0.03281 0.02635 -0.0848 0.2387 1.0000
12.500 1.6792 0.03417 0.02776 -0.0839 0.2340 1.0000
12.750 1.6867 0.03582 0.02943 -0.0829 0.2283 1.0000
13.000 1.6910 0.03779 0.03141 -0.0818 0.2229 1.0000
13.250 1.6969 0.03967 0.03332 -0.0809 0.2167 1.0000
13.500 1.6970 0.04212 0.03578 -0.0798 0.2105 1.0000
13.750 1.7011 0.04424 0.03793 -0.0789 0.2043 1.0000
14.000 1.6986 0.04707 0.04077 -0.0779 0.1979 1.0000
14.250 1.6982 0.04975 0.04348 -0.0771 0.1921 1.0000
14.500 1.6940 0.05286 0.04660 -0.0763 0.1865 1.0000
14.750 1.6914 0.05585 0.04963 -0.0756 0.1819 1.0000
15.000 1.6894 0.05882 0.05264 -0.0750 0.1775 1.0000
15.250 1.6831 0.06233 0.05617 -0.0744 0.1735 1.0000
15.500 1.6809 0.06539 0.05928 -0.0740 0.1704 1.0000
15.750 1.6809 0.06821 0.06215 -0.0737 0.1674 1.0000
16.000 1.6775 0.07147 0.06545 -0.0733 0.1646 1.0000
16.250 1.6735 0.07481 0.06883 -0.0731 0.1621 1.0000
16.500 1.6700 0.07810 0.07217 -0.0729 0.1599 1.0000
16.750 1.6731 0.08062 0.07475 -0.0728 0.1582 1.0000
17.000 1.6732 0.08352 0.07772 -0.0727 0.1564 1.0000
17.250 1.6739 0.08634 0.08060 -0.0726 0.1546 1.0000
17.500 1.6722 0.08950 0.08380 -0.0727 0.1527 1.0000
17.750 1.6699 0.09272 0.08707 -0.0728 0.1509 1.0000
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