USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 AIRFOIL (usa35-il) Reynolds number: 500,000 Max Cl/Cd: 97.69 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35-il-500000.txt Download as CSV file: xf-usa35-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0077 0.10106 0.09803 -0.0826 0.8377 0.0455
-10.000 0.0002 0.09846 0.09540 -0.0837 0.8268 0.0462
-9.750 -0.0278 0.08951 0.08639 -0.0919 0.8183 0.0487
-9.500 -0.0146 0.08771 0.08456 -0.0915 0.8082 0.0489
-9.250 -0.0018 0.08603 0.08282 -0.0913 0.7978 0.0491
-9.000 0.0107 0.08421 0.08099 -0.0915 0.7879 0.0494
-8.750 0.0215 0.08224 0.07896 -0.0920 0.7774 0.0498
-8.500 0.0308 0.07988 0.07658 -0.0931 0.7674 0.0504
-8.250 -0.1918 0.02360 0.01813 -0.1344 0.7663 0.0435
-8.000 -0.1720 0.02196 0.01608 -0.1339 0.7569 0.0440
-7.750 -0.1498 0.02054 0.01447 -0.1335 0.7476 0.0444
-7.500 -0.1248 0.01984 0.01370 -0.1332 0.7372 0.0448
-7.250 -0.0990 0.01932 0.01310 -0.1330 0.7266 0.0453
-7.000 -0.0733 0.01881 0.01249 -0.1326 0.7145 0.0458
-6.750 -0.0475 0.01825 0.01181 -0.1323 0.7022 0.0465
-6.500 -0.0220 0.01767 0.01104 -0.1319 0.6897 0.0472
-6.250 0.0040 0.01707 0.01025 -0.1315 0.6763 0.0480
-6.000 0.0303 0.01665 0.00961 -0.1311 0.6634 0.0487
-5.500 0.0828 0.01577 0.00864 -0.1306 0.6382 0.0503
-5.250 0.1096 0.01558 0.00834 -0.1303 0.6271 0.0513
-5.000 0.1367 0.01530 0.00795 -0.1300 0.6167 0.0525
-4.750 0.1638 0.01509 0.00756 -0.1297 0.6078 0.0535
-4.500 0.1907 0.01460 0.00708 -0.1295 0.5995 0.0546
-4.250 0.2176 0.01444 0.00686 -0.1292 0.5909 0.0557
-4.000 0.2453 0.01424 0.00661 -0.1291 0.5832 0.0571
-3.750 0.2729 0.01408 0.00634 -0.1288 0.5759 0.0586
-3.500 0.2996 0.01381 0.00602 -0.1286 0.5695 0.0601
-3.250 0.3278 0.01367 0.00590 -0.1285 0.5647 0.0618
-3.000 0.3560 0.01356 0.00574 -0.1284 0.5598 0.0639
-2.750 0.3834 0.01332 0.00549 -0.1283 0.5549 0.0658
-2.500 0.4111 0.01325 0.00538 -0.1281 0.5503 0.0678
-2.250 0.4394 0.01318 0.00526 -0.1281 0.5466 0.0700
-2.000 0.4673 0.01295 0.00508 -0.1280 0.5429 0.0725
-1.750 0.4955 0.01287 0.00500 -0.1280 0.5389 0.0753
-1.500 0.5234 0.01277 0.00487 -0.1279 0.5348 0.0782
-1.250 0.5510 0.01271 0.00479 -0.1278 0.5306 0.0812
-1.000 0.5794 0.01272 0.00476 -0.1278 0.5269 0.0847
-0.750 0.6074 0.01254 0.00466 -0.1278 0.5238 0.0889
-0.500 0.6356 0.01247 0.00460 -0.1277 0.5204 0.0934
-0.250 0.6635 0.01239 0.00455 -0.1277 0.5168 0.0993
0.000 0.6914 0.01234 0.00451 -0.1276 0.5131 0.1070
0.250 0.7193 0.01236 0.00452 -0.1276 0.5088 0.1197
0.500 0.7470 0.01217 0.00454 -0.1276 0.5055 0.1657
0.750 0.7743 0.01193 0.00460 -0.1276 0.5019 0.2514
1.000 0.8015 0.01172 0.00466 -0.1276 0.4982 0.3439
1.250 0.8281 0.01146 0.00477 -0.1276 0.4944 0.4770
1.500 0.8532 0.01115 0.00492 -0.1272 0.4905 0.6492
1.750 0.8706 0.01075 0.00515 -0.1245 0.4868 0.8721
2.000 0.9104 0.01069 0.00519 -0.1267 0.4830 1.0000
2.250 0.9368 0.01079 0.00524 -0.1263 0.4789 1.0000
2.500 0.9630 0.01090 0.00530 -0.1260 0.4746 1.0000
2.750 0.9890 0.01109 0.00538 -0.1256 0.4699 1.0000
3.000 1.0151 0.01121 0.00548 -0.1253 0.4655 1.0000
3.250 1.0410 0.01130 0.00556 -0.1249 0.4607 1.0000
3.500 1.0663 0.01142 0.00563 -0.1244 0.4553 1.0000
3.750 1.0907 0.01163 0.00574 -0.1238 0.4493 1.0000
4.000 1.1160 0.01171 0.00585 -0.1233 0.4438 1.0000
4.250 1.1404 0.01185 0.00595 -0.1227 0.4374 1.0000
4.500 1.1634 0.01207 0.00609 -0.1218 0.4313 1.0000
4.750 1.1879 0.01220 0.00623 -0.1212 0.4248 1.0000
5.000 1.2103 0.01239 0.00637 -0.1203 0.4173 1.0000
5.250 1.2316 0.01262 0.00655 -0.1192 0.4101 1.0000
5.500 1.2524 0.01282 0.00674 -0.1179 0.4027 1.0000
5.750 1.2708 0.01314 0.00698 -0.1163 0.3957 1.0000
6.000 1.2924 0.01338 0.00722 -0.1153 0.3889 1.0000
6.250 1.3115 0.01372 0.00751 -0.1139 0.3817 1.0000
6.500 1.3308 0.01408 0.00782 -0.1126 0.3751 1.0000
6.750 1.3509 0.01442 0.00815 -0.1115 0.3685 1.0000
7.000 1.3682 0.01489 0.00855 -0.1100 0.3621 1.0000
7.250 1.3886 0.01526 0.00892 -0.1090 0.3568 1.0000
7.500 1.4083 0.01566 0.00931 -0.1079 0.3518 1.0000
7.750 1.4259 0.01616 0.00977 -0.1066 0.3471 1.0000
8.000 1.4439 0.01667 0.01026 -0.1053 0.3428 1.0000
8.250 1.4642 0.01707 0.01069 -0.1045 0.3389 1.0000
8.500 1.4827 0.01757 0.01119 -0.1034 0.3347 1.0000
8.750 1.4994 0.01816 0.01175 -0.1021 0.3306 1.0000
9.000 1.5152 0.01882 0.01239 -0.1007 0.3266 1.0000
9.250 1.5348 0.01929 0.01291 -0.0999 0.3232 1.0000
9.500 1.5524 0.01986 0.01350 -0.0989 0.3194 1.0000
9.750 1.5682 0.02054 0.01418 -0.0977 0.3156 1.0000
10.000 1.5823 0.02135 0.01496 -0.0963 0.3118 1.0000
10.250 1.5989 0.02203 0.01567 -0.0953 0.3086 1.0000
10.500 1.6163 0.02267 0.01637 -0.0944 0.3054 1.0000
10.750 1.6315 0.02344 0.01718 -0.0933 0.3018 1.0000
11.000 1.6449 0.02435 0.01807 -0.0921 0.2981 1.0000
11.250 1.6560 0.02541 0.01911 -0.0907 0.2941 1.0000
11.500 1.6721 0.02619 0.01998 -0.0899 0.2911 1.0000
11.750 1.6861 0.02711 0.02096 -0.0890 0.2874 1.0000
12.000 1.6978 0.02820 0.02206 -0.0878 0.2833 1.0000
12.250 1.7056 0.02958 0.02342 -0.0864 0.2791 1.0000
12.500 1.7186 0.03065 0.02458 -0.0856 0.2752 1.0000
12.750 1.7298 0.03188 0.02586 -0.0846 0.2707 1.0000
13.000 1.7374 0.03340 0.02739 -0.0835 0.2660 1.0000
13.250 1.7438 0.03506 0.02906 -0.0823 0.2615 1.0000
13.500 1.7539 0.03650 0.03059 -0.0816 0.2564 1.0000
13.750 1.7586 0.03841 0.03251 -0.0805 0.2509 1.0000
14.000 1.7620 0.04048 0.03461 -0.0795 0.2452 1.0000
14.250 1.7658 0.04260 0.03678 -0.0787 0.2385 1.0000
14.500 1.7635 0.04531 0.03948 -0.0776 0.2320 1.0000
14.750 1.7658 0.04767 0.04190 -0.0769 0.2249 1.0000
15.000 1.7598 0.05087 0.04508 -0.0759 0.2184 1.0000
15.250 1.7599 0.05354 0.04781 -0.0753 0.2122 1.0000
15.500 1.7522 0.05704 0.05130 -0.0745 0.2064 1.0000
15.750 1.7521 0.05979 0.05410 -0.0740 0.2015 1.0000
16.000 1.7479 0.06298 0.05732 -0.0734 0.1968 1.0000
16.250 1.7397 0.06662 0.06095 -0.0729 0.1925 1.0000
16.500 1.7419 0.06917 0.06357 -0.0726 0.1894 1.0000
16.750 1.7405 0.07214 0.06659 -0.0723 0.1861 1.0000
17.000 1.7372 0.07531 0.06977 -0.0720 0.1831 1.0000
17.250 1.7331 0.07849 0.07294 -0.0716 0.1801 1.0000
17.500 1.7361 0.08100 0.07554 -0.0715 0.1779 1.0000
17.750 1.7366 0.08380 0.07841 -0.0715 0.1757 1.0000
18.000 1.7376 0.08652 0.08117 -0.0714 0.1734 1.0000
18.250 1.7374 0.08936 0.08404 -0.0714 0.1713 1.0000
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