USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 35 A AIRFOIL (usa35a-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.63 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35a-il-1000000-n5.txt Download as CSV file: xf-usa35a-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8651 0.03092 0.02706 -0.1366 0.9003 0.0256
-15.000 -0.8686 0.02815 0.02406 -0.1380 0.8791 0.0257
-14.750 -0.8639 0.02666 0.02240 -0.1372 0.8608 0.0258
-14.500 -0.8511 0.02543 0.02102 -0.1368 0.8460 0.0259
-14.250 -0.8355 0.02438 0.01983 -0.1364 0.8337 0.0260
-14.000 -0.8176 0.02344 0.01878 -0.1360 0.8237 0.0261
-13.750 -0.7986 0.02259 0.01781 -0.1355 0.8147 0.0262
-13.500 -0.7779 0.02180 0.01692 -0.1352 0.8071 0.0263
-13.250 -0.7565 0.02108 0.01610 -0.1348 0.7988 0.0265
-13.000 -0.7343 0.02041 0.01533 -0.1344 0.7917 0.0266
-12.750 -0.7112 0.01977 0.01461 -0.1341 0.7842 0.0267
-12.500 -0.6878 0.01919 0.01394 -0.1338 0.7756 0.0269
-12.250 -0.6636 0.01866 0.01332 -0.1335 0.7682 0.0270
-12.000 -0.6387 0.01816 0.01274 -0.1332 0.7601 0.0271
-11.750 -0.6137 0.01771 0.01219 -0.1329 0.7520 0.0273
-11.500 -0.5881 0.01727 0.01168 -0.1326 0.7453 0.0274
-11.250 -0.5628 0.01677 0.01111 -0.1324 0.7372 0.0275
-10.750 -0.5120 0.01580 0.01000 -0.1318 0.7212 0.0280
-10.500 -0.4859 0.01541 0.00954 -0.1316 0.7118 0.0282
-10.250 -0.4593 0.01506 0.00912 -0.1314 0.7031 0.0284
-10.000 -0.4325 0.01473 0.00873 -0.1312 0.6928 0.0286
-9.750 -0.4056 0.01443 0.00836 -0.1310 0.6826 0.0289
-9.500 -0.3786 0.01416 0.00801 -0.1308 0.6702 0.0291
-9.250 -0.3515 0.01391 0.00768 -0.1305 0.6573 0.0294
-9.000 -0.3245 0.01368 0.00736 -0.1303 0.6428 0.0296
-8.750 -0.2972 0.01346 0.00706 -0.1301 0.6279 0.0299
-8.500 -0.2698 0.01326 0.00677 -0.1299 0.6143 0.0302
-8.250 -0.2424 0.01307 0.00649 -0.1297 0.6007 0.0304
-8.000 -0.2148 0.01290 0.00624 -0.1295 0.5878 0.0307
-7.750 -0.1870 0.01273 0.00599 -0.1294 0.5773 0.0309
-7.500 -0.1594 0.01252 0.00572 -0.1292 0.5672 0.0313
-7.250 -0.1315 0.01233 0.00549 -0.1291 0.5594 0.0317
-7.000 -0.1032 0.01216 0.00528 -0.1290 0.5524 0.0322
-6.750 -0.0751 0.01202 0.00509 -0.1289 0.5452 0.0326
-6.500 -0.0467 0.01187 0.00491 -0.1289 0.5394 0.0331
-6.250 -0.0181 0.01173 0.00474 -0.1289 0.5344 0.0336
-6.000 0.0105 0.01160 0.00457 -0.1288 0.5297 0.0342
-5.750 0.0390 0.01150 0.00442 -0.1288 0.5246 0.0346
-5.500 0.0674 0.01137 0.00427 -0.1287 0.5196 0.0354
-5.250 0.0962 0.01124 0.00413 -0.1287 0.5152 0.0363
-5.000 0.1249 0.01114 0.00401 -0.1287 0.5103 0.0372
-4.750 0.1535 0.01107 0.00390 -0.1287 0.5055 0.0381
-4.250 0.2109 0.01089 0.00369 -0.1287 0.4970 0.0400
-4.000 0.2400 0.01080 0.00360 -0.1287 0.4939 0.0413
-3.750 0.2690 0.01073 0.00351 -0.1287 0.4908 0.0425
-3.500 0.2978 0.01066 0.00344 -0.1288 0.4875 0.0438
-3.250 0.3264 0.01061 0.00338 -0.1288 0.4840 0.0454
-3.000 0.3550 0.01059 0.00332 -0.1287 0.4804 0.0469
-2.750 0.3840 0.01052 0.00327 -0.1288 0.4781 0.0486
-2.500 0.4131 0.01047 0.00323 -0.1289 0.4763 0.0505
-2.250 0.4422 0.01042 0.00318 -0.1290 0.4740 0.0523
-2.000 0.4712 0.01037 0.00314 -0.1290 0.4712 0.0543
-1.750 0.4999 0.01035 0.00311 -0.1290 0.4679 0.0562
-1.500 0.5285 0.01033 0.00309 -0.1290 0.4643 0.0580
-1.250 0.5568 0.01033 0.00308 -0.1290 0.4606 0.0603
-1.000 0.5855 0.01032 0.00307 -0.1290 0.4581 0.0626
-0.750 0.6145 0.01029 0.00306 -0.1291 0.4557 0.0654
-0.500 0.6433 0.01027 0.00305 -0.1292 0.4528 0.0680
-0.250 0.6718 0.01026 0.00306 -0.1292 0.4494 0.0711
0.000 0.7001 0.01028 0.00307 -0.1292 0.4457 0.0746
0.250 0.7279 0.01030 0.00309 -0.1291 0.4416 0.0789
0.500 0.7563 0.01031 0.00311 -0.1291 0.4382 0.0834
0.750 0.7847 0.01031 0.00313 -0.1291 0.4340 0.0888
1.000 0.8126 0.01032 0.00315 -0.1291 0.4288 0.0963
1.250 0.8399 0.01036 0.00320 -0.1289 0.4235 0.1070
1.500 0.8677 0.01034 0.00324 -0.1289 0.4192 0.1310
1.750 0.8953 0.01028 0.00332 -0.1289 0.4135 0.1821
2.000 0.9218 0.01036 0.00340 -0.1287 0.4056 0.2056
2.250 0.9487 0.01041 0.00349 -0.1285 0.3977 0.2267
2.500 0.9743 0.01050 0.00360 -0.1281 0.3876 0.2620
2.750 1.0003 0.01049 0.00374 -0.1279 0.3777 0.3361
3.000 1.0250 0.01050 0.00393 -0.1275 0.3670 0.4374
3.250 1.0497 0.01062 0.00411 -0.1270 0.3561 0.4925
3.500 1.0746 0.01065 0.00429 -0.1266 0.3482 0.5678
3.750 1.0978 0.01040 0.00457 -0.1259 0.3408 0.7875
4.000 1.1185 0.01025 0.00478 -0.1242 0.3348 1.0000
4.250 1.1434 0.01043 0.00493 -0.1237 0.3298 1.0000
4.500 1.1671 0.01066 0.00511 -0.1230 0.3239 1.0000
4.750 1.1891 0.01092 0.00531 -0.1220 0.3179 1.0000
5.000 1.2121 0.01111 0.00548 -0.1211 0.3137 1.0000
5.250 1.2346 0.01133 0.00568 -0.1202 0.3099 1.0000
5.500 1.2568 0.01158 0.00590 -0.1193 0.3062 1.0000
5.750 1.2784 0.01186 0.00614 -0.1183 0.3023 1.0000
6.000 1.3014 0.01209 0.00636 -0.1175 0.2993 1.0000
6.250 1.3242 0.01233 0.00660 -0.1168 0.2957 1.0000
6.500 1.3459 0.01263 0.00687 -0.1159 0.2917 1.0000
6.750 1.3668 0.01296 0.00717 -0.1149 0.2879 1.0000
7.000 1.3878 0.01329 0.00749 -0.1139 0.2842 1.0000
7.250 1.4102 0.01357 0.00777 -0.1132 0.2816 1.0000
7.500 1.4322 0.01387 0.00807 -0.1125 0.2788 1.0000
7.750 1.4532 0.01421 0.00841 -0.1116 0.2758 1.0000
8.000 1.4732 0.01461 0.00879 -0.1106 0.2726 1.0000
8.250 1.4926 0.01505 0.00922 -0.1096 0.2693 1.0000
8.500 1.5134 0.01542 0.00960 -0.1088 0.2669 1.0000
8.750 1.5340 0.01581 0.01000 -0.1080 0.2643 1.0000
9.000 1.5538 0.01624 0.01044 -0.1071 0.2610 1.0000
9.250 1.5719 0.01677 0.01096 -0.1061 0.2574 1.0000
9.500 1.5888 0.01738 0.01156 -0.1049 0.2534 1.0000
9.750 1.6079 0.01788 0.01208 -0.1040 0.2503 1.0000
10.000 1.6255 0.01847 0.01267 -0.1030 0.2459 1.0000
10.250 1.6409 0.01920 0.01339 -0.1018 0.2409 1.0000
10.500 1.6561 0.01997 0.01415 -0.1006 0.2365 1.0000
10.750 1.6723 0.02069 0.01488 -0.0996 0.2315 1.0000
11.000 1.6845 0.02169 0.01586 -0.0983 0.2255 1.0000
11.250 1.6979 0.02262 0.01679 -0.0971 0.2199 1.0000
11.500 1.7080 0.02380 0.01795 -0.0956 0.2124 1.0000
11.750 1.7175 0.02506 0.01920 -0.0942 0.2051 1.0000
12.000 1.7236 0.02658 0.02070 -0.0926 0.1968 1.0000
12.250 1.7295 0.02817 0.02227 -0.0911 0.1887 1.0000
12.500 1.7329 0.03002 0.02410 -0.0895 0.1813 1.0000
12.750 1.7370 0.03187 0.02595 -0.0880 0.1751 1.0000
13.000 1.7418 0.03370 0.02779 -0.0867 0.1704 1.0000
13.250 1.7469 0.03557 0.02968 -0.0856 0.1666 1.0000
13.500 1.7506 0.03761 0.03175 -0.0845 0.1631 1.0000
13.750 1.7540 0.03971 0.03387 -0.0834 0.1598 1.0000
14.000 1.7595 0.04169 0.03590 -0.0826 0.1575 1.0000
14.250 1.7639 0.04378 0.03802 -0.0817 0.1552 1.0000
14.500 1.7676 0.04598 0.04026 -0.0809 0.1533 1.0000
14.750 1.7687 0.04849 0.04282 -0.0802 0.1513 1.0000
15.000 1.7690 0.05112 0.04549 -0.0794 0.1491 1.0000
15.250 1.7731 0.05337 0.04780 -0.0789 0.1478 1.0000
15.500 1.7761 0.05577 0.05026 -0.0783 0.1465 1.0000
15.750 1.7792 0.05817 0.05271 -0.0779 0.1450 1.0000
16.000 1.7796 0.06090 0.05550 -0.0774 0.1434 1.0000
16.250 1.7793 0.06373 0.05838 -0.0770 0.1419 1.0000
16.500 1.7784 0.06661 0.06131 -0.0766 0.1405 1.0000
16.750 1.7747 0.06985 0.06460 -0.0762 0.1389 1.0000
17.000 1.7729 0.07286 0.06766 -0.0759 0.1374 1.0000
17.250 1.7738 0.07562 0.07050 -0.0757 0.1365 1.0000
17.500 1.7766 0.07813 0.07307 -0.0756 0.1353 1.0000
17.750 1.7754 0.08112 0.07612 -0.0755 0.1338 1.0000
18.000 1.7747 0.08404 0.07909 -0.0754 0.1321 1.0000
18.250 1.7721 0.08723 0.08233 -0.0753 0.1305 1.0000
18.500 1.7684 0.09058 0.08573 -0.0754 0.1290 1.0000
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