USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 A AIRFOIL (usa35a-il) Reynolds number: 500,000 Max Cl/Cd: 97.8 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35a-il-500000.txt Download as CSV file: xf-usa35a-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0107 0.09652 0.09346 -0.0856 0.8274 0.0466
-9.750 -0.2085 0.04642 0.04309 -0.1259 0.8229 0.0416
-9.500 -0.2519 0.03615 0.03227 -0.1342 0.8116 0.0412
-9.250 -0.2731 0.02848 0.02375 -0.1357 0.8015 0.0412
-9.000 -0.2625 0.02562 0.02037 -0.1354 0.7931 0.0415
-8.750 -0.2451 0.02357 0.01809 -0.1351 0.7841 0.0419
-8.500 -0.2223 0.02260 0.01699 -0.1347 0.7754 0.0422
-8.250 -0.1979 0.02187 0.01619 -0.1345 0.7665 0.0426
-8.000 -0.1735 0.02118 0.01539 -0.1341 0.7569 0.0430
-7.750 -0.1485 0.02050 0.01460 -0.1338 0.7475 0.0434
-7.500 -0.1238 0.01974 0.01369 -0.1335 0.7371 0.0440
-7.250 -0.0990 0.01895 0.01270 -0.1331 0.7268 0.0446
-7.000 -0.0739 0.01824 0.01177 -0.1327 0.7150 0.0454
-6.750 -0.0481 0.01766 0.01096 -0.1323 0.7029 0.0461
-6.250 0.0036 0.01657 0.00976 -0.1317 0.6764 0.0474
-6.000 0.0301 0.01624 0.00932 -0.1314 0.6634 0.0481
-5.750 0.0564 0.01590 0.00885 -0.1310 0.6503 0.0489
-5.500 0.0833 0.01552 0.00835 -0.1307 0.6383 0.0499
-5.250 0.1100 0.01528 0.00790 -0.1303 0.6272 0.0507
-5.000 0.1366 0.01477 0.00739 -0.1301 0.6171 0.0517
-4.500 0.1912 0.01439 0.00689 -0.1297 0.5995 0.0540
-4.250 0.2185 0.01425 0.00662 -0.1294 0.5910 0.0555
-4.000 0.2455 0.01394 0.00630 -0.1292 0.5833 0.0570
-3.750 0.2731 0.01381 0.00615 -0.1290 0.5759 0.0585
-3.500 0.3006 0.01371 0.00594 -0.1288 0.5695 0.0604
-3.250 0.3282 0.01347 0.00567 -0.1286 0.5646 0.0622
-3.000 0.3563 0.01331 0.00555 -0.1286 0.5600 0.0641
-2.750 0.3844 0.01323 0.00540 -0.1285 0.5551 0.0664
-2.500 0.4119 0.01307 0.00522 -0.1283 0.5505 0.0688
-2.250 0.4399 0.01306 0.00517 -0.1283 0.5460 0.0716
-2.000 0.4682 0.01290 0.00502 -0.1282 0.5427 0.0745
-1.750 0.4963 0.01278 0.00494 -0.1282 0.5390 0.0774
-1.500 0.5246 0.01273 0.00485 -0.1281 0.5351 0.0806
-1.250 0.5522 0.01262 0.00475 -0.1280 0.5310 0.0844
-1.000 0.5803 0.01267 0.00473 -0.1280 0.5265 0.0882
-0.750 0.6083 0.01253 0.00465 -0.1280 0.5235 0.0928
-0.500 0.6365 0.01244 0.00458 -0.1280 0.5202 0.0980
-0.250 0.6646 0.01237 0.00454 -0.1279 0.5167 0.1043
0.000 0.6925 0.01230 0.00450 -0.1279 0.5131 0.1127
0.250 0.7202 0.01226 0.00448 -0.1278 0.5093 0.1260
0.500 0.7481 0.01218 0.00456 -0.1279 0.5052 0.1786
0.750 0.7755 0.01198 0.00461 -0.1279 0.5020 0.2469
1.000 0.8027 0.01175 0.00467 -0.1279 0.4982 0.3360
1.250 0.8294 0.01150 0.00478 -0.1278 0.4943 0.4702
1.500 0.8554 0.01125 0.00488 -0.1276 0.4905 0.5925
1.750 0.8766 0.01091 0.00510 -0.1261 0.4863 0.8081
2.000 0.9113 0.01072 0.00520 -0.1269 0.4828 1.0000
2.250 0.9378 0.01080 0.00525 -0.1266 0.4788 1.0000
2.500 0.9641 0.01090 0.00531 -0.1262 0.4746 1.0000
2.750 0.9902 0.01104 0.00538 -0.1259 0.4702 1.0000
3.000 1.0163 0.01125 0.00549 -0.1255 0.4654 1.0000
3.250 1.0421 0.01132 0.00557 -0.1251 0.4609 1.0000
3.500 1.0675 0.01142 0.00564 -0.1247 0.4553 1.0000
3.750 1.0919 0.01159 0.00573 -0.1240 0.4494 1.0000
4.000 1.1168 0.01173 0.00585 -0.1235 0.4437 1.0000
4.250 1.1417 0.01185 0.00596 -0.1229 0.4374 1.0000
4.500 1.1649 0.01204 0.00608 -0.1221 0.4311 1.0000
4.750 1.1887 0.01221 0.00623 -0.1214 0.4246 1.0000
5.000 1.2118 0.01239 0.00638 -0.1206 0.4173 1.0000
5.250 1.2320 0.01266 0.00657 -0.1193 0.4103 1.0000
5.500 1.2539 0.01283 0.00675 -0.1182 0.4031 1.0000
5.750 1.2727 0.01312 0.00697 -0.1167 0.3955 1.0000
6.000 1.2931 0.01340 0.00723 -0.1155 0.3885 1.0000
6.250 1.3129 0.01371 0.00750 -0.1142 0.3814 1.0000
6.500 1.3311 0.01412 0.00785 -0.1127 0.3750 1.0000
6.750 1.3523 0.01442 0.00816 -0.1118 0.3689 1.0000
7.000 1.3706 0.01484 0.00853 -0.1104 0.3624 1.0000
7.250 1.3888 0.01530 0.00895 -0.1091 0.3568 1.0000
7.500 1.4093 0.01567 0.00932 -0.1082 0.3518 1.0000
7.750 1.4278 0.01613 0.00976 -0.1069 0.3469 1.0000
8.000 1.4444 0.01670 0.01028 -0.1055 0.3423 1.0000
8.250 1.4644 0.01712 0.01073 -0.1046 0.3386 1.0000
8.500 1.4837 0.01758 0.01120 -0.1036 0.3346 1.0000
8.750 1.5015 0.01811 0.01173 -0.1025 0.3306 1.0000
9.000 1.5171 0.01877 0.01236 -0.1011 0.3267 1.0000
9.250 1.5345 0.01937 0.01296 -0.1000 0.3231 1.0000
9.500 1.5533 0.01988 0.01352 -0.0991 0.3197 1.0000
9.750 1.5701 0.02051 0.01416 -0.0980 0.3159 1.0000
10.000 1.5852 0.02125 0.01490 -0.0968 0.3121 1.0000
10.250 1.5982 0.02213 0.01574 -0.0953 0.3080 1.0000
10.500 1.6160 0.02275 0.01643 -0.0945 0.3051 1.0000
10.750 1.6323 0.02346 0.01719 -0.0936 0.3017 1.0000
11.000 1.6468 0.02430 0.01805 -0.0925 0.2980 1.0000
11.250 1.6587 0.02532 0.01906 -0.0911 0.2943 1.0000
11.500 1.6712 0.02631 0.02006 -0.0899 0.2907 1.0000
11.750 1.6861 0.02718 0.02101 -0.0891 0.2873 1.0000
12.000 1.6993 0.02817 0.02205 -0.0881 0.2833 1.0000
12.250 1.7091 0.02942 0.02331 -0.0869 0.2793 1.0000
12.500 1.7174 0.03079 0.02467 -0.0856 0.2751 1.0000
12.750 1.7304 0.03191 0.02589 -0.0848 0.2711 1.0000
13.000 1.7400 0.03328 0.02730 -0.0838 0.2662 1.0000
13.250 1.7445 0.03509 0.02910 -0.0825 0.2613 1.0000
13.500 1.7538 0.03659 0.03067 -0.0817 0.2565 1.0000
13.750 1.7606 0.03833 0.03245 -0.0808 0.2507 1.0000
14.000 1.7601 0.04073 0.03483 -0.0796 0.2449 1.0000
14.250 1.7668 0.04260 0.03678 -0.0789 0.2385 1.0000
14.500 1.7639 0.04537 0.03954 -0.0778 0.2317 1.0000
14.750 1.7665 0.04770 0.04193 -0.0771 0.2249 1.0000
15.000 1.7611 0.05086 0.04508 -0.0761 0.2182 1.0000
15.250 1.7601 0.05362 0.04789 -0.0755 0.2121 1.0000
15.500 1.7554 0.05681 0.05110 -0.0747 0.2064 1.0000
15.750 1.7513 0.05997 0.05427 -0.0741 0.2016 1.0000
16.000 1.7499 0.06288 0.05723 -0.0736 0.1971 1.0000
16.250 1.7440 0.06628 0.06063 -0.0731 0.1929 1.0000
16.500 1.7404 0.06943 0.06380 -0.0727 0.1893 1.0000
16.750 1.7408 0.07222 0.06667 -0.0724 0.1861 1.0000
17.000 1.7399 0.07512 0.06960 -0.0722 0.1831 1.0000
17.250 1.7359 0.07836 0.07286 -0.0719 0.1804 1.0000
17.500 1.7345 0.08123 0.07572 -0.0717 0.1775 1.0000
17.750 1.7362 0.08393 0.07851 -0.0716 0.1756 1.0000
18.000 1.7380 0.08658 0.08123 -0.0716 0.1734 1.0000
18.250 1.7390 0.08930 0.08400 -0.0716 0.1712 1.0000
18.500 1.7381 0.09224 0.08696 -0.0717 0.1691 1.0000
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