USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 AIRFOIL (usa35-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.33 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35-il-1000000.txt Download as CSV file: xf-usa35-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6713 0.03344 0.03017 -0.1371 0.9263 0.0312
-13.500 -0.6815 0.03012 0.02660 -0.1387 0.9082 0.0313
-13.250 -0.6793 0.02825 0.02454 -0.1381 0.8939 0.0314
-13.000 -0.6687 0.02674 0.02283 -0.1377 0.8808 0.0315
-12.750 -0.6541 0.02548 0.02141 -0.1373 0.8695 0.0316
-12.250 -0.6175 0.02353 0.01915 -0.1365 0.8488 0.0319
-12.000 -0.6056 0.02159 0.01698 -0.1358 0.8386 0.0322
-11.750 -0.5856 0.02054 0.01583 -0.1353 0.8304 0.0324
-11.500 -0.5631 0.01984 0.01504 -0.1349 0.8218 0.0327
-11.250 -0.5393 0.01926 0.01439 -0.1346 0.8140 0.0329
-11.000 -0.5146 0.01873 0.01380 -0.1343 0.8060 0.0331
-10.750 -0.4900 0.01825 0.01323 -0.1340 0.7975 0.0334
-10.500 -0.4645 0.01775 0.01267 -0.1337 0.7903 0.0336
-10.250 -0.4390 0.01727 0.01210 -0.1335 0.7824 0.0339
-10.000 -0.4135 0.01682 0.01155 -0.1332 0.7745 0.0342
-9.750 -0.3873 0.01633 0.01100 -0.1330 0.7675 0.0345
-9.500 -0.3611 0.01591 0.01048 -0.1327 0.7592 0.0348
-9.250 -0.3344 0.01555 0.01003 -0.1325 0.7513 0.0352
-9.000 -0.3071 0.01522 0.00963 -0.1324 0.7430 0.0355
-8.750 -0.2801 0.01496 0.00926 -0.1321 0.7336 0.0357
-8.500 -0.2551 0.01416 0.00839 -0.1318 0.7252 0.0362
-8.250 -0.2285 0.01379 0.00796 -0.1316 0.7147 0.0366
-8.000 -0.2010 0.01351 0.00764 -0.1314 0.7042 0.0370
-7.500 -0.1460 0.01306 0.00705 -0.1310 0.6791 0.0379
-7.250 -0.1186 0.01285 0.00676 -0.1308 0.6658 0.0384
-7.000 -0.0914 0.01267 0.00647 -0.1306 0.6509 0.0390
-6.750 -0.0636 0.01250 0.00621 -0.1304 0.6364 0.0394
-6.500 -0.0361 0.01233 0.00594 -0.1302 0.6218 0.0398
-6.250 -0.0097 0.01200 0.00554 -0.1299 0.6076 0.0406
-6.000 0.0181 0.01186 0.00535 -0.1297 0.5948 0.0413
-5.750 0.0460 0.01176 0.00519 -0.1296 0.5836 0.0420
-5.500 0.0738 0.01167 0.00503 -0.1294 0.5731 0.0428
-5.250 0.1021 0.01158 0.00487 -0.1293 0.5646 0.0436
-5.000 0.1301 0.01143 0.00467 -0.1292 0.5568 0.0444
-4.750 0.1576 0.01131 0.00450 -0.1291 0.5487 0.0455
-4.500 0.1866 0.01120 0.00439 -0.1291 0.5438 0.0465
-4.250 0.2152 0.01112 0.00427 -0.1291 0.5384 0.0476
-4.000 0.2435 0.01109 0.00418 -0.1290 0.5328 0.0486
-3.750 0.2713 0.01092 0.00400 -0.1289 0.5278 0.0500
-3.500 0.3005 0.01082 0.00391 -0.1290 0.5252 0.0513
-3.250 0.3296 0.01075 0.00383 -0.1290 0.5221 0.0528
-3.000 0.3582 0.01065 0.00371 -0.1290 0.5186 0.0543
-2.750 0.3867 0.01058 0.00364 -0.1290 0.5148 0.0560
-2.500 0.4149 0.01059 0.00361 -0.1289 0.5106 0.0578
-2.250 0.4434 0.01053 0.00354 -0.1289 0.5071 0.0597
-2.000 0.4725 0.01044 0.00347 -0.1290 0.5051 0.0617
-1.750 0.5017 0.01039 0.00343 -0.1291 0.5026 0.0637
-1.500 0.5305 0.01031 0.00335 -0.1292 0.4997 0.0660
-1.250 0.5591 0.01028 0.00333 -0.1292 0.4966 0.0685
-1.000 0.5874 0.01029 0.00331 -0.1291 0.4931 0.0709
-0.750 0.6151 0.01029 0.00330 -0.1290 0.4889 0.0741
-0.500 0.6440 0.01027 0.00328 -0.1291 0.4864 0.0771
-0.250 0.6730 0.01018 0.00324 -0.1292 0.4841 0.0815
0.000 0.7019 0.01014 0.00322 -0.1293 0.4813 0.0862
0.250 0.7304 0.01011 0.00321 -0.1294 0.4782 0.0924
0.500 0.7585 0.01008 0.00320 -0.1293 0.4748 0.1035
0.750 0.7859 0.01002 0.00323 -0.1293 0.4710 0.1359
1.000 0.8136 0.00989 0.00331 -0.1293 0.4675 0.2050
1.250 0.8423 0.00978 0.00334 -0.1295 0.4650 0.2523
1.500 0.8706 0.00963 0.00339 -0.1296 0.4616 0.3218
1.750 0.8982 0.00945 0.00347 -0.1297 0.4576 0.4269
2.000 0.9250 0.00930 0.00358 -0.1296 0.4531 0.5417
2.250 0.9505 0.00903 0.00374 -0.1293 0.4485 0.7100
2.500 0.9707 0.00864 0.00388 -0.1274 0.4448 0.9001
2.750 1.0055 0.00864 0.00393 -0.1286 0.4389 1.0000
3.000 1.0313 0.00879 0.00401 -0.1282 0.4327 1.0000
3.250 1.0584 0.00889 0.00408 -0.1280 0.4277 1.0000
3.500 1.0854 0.00901 0.00416 -0.1279 0.4214 1.0000
3.750 1.1104 0.00919 0.00427 -0.1274 0.4138 1.0000
4.000 1.1370 0.00932 0.00436 -0.1271 0.4068 1.0000
4.250 1.1616 0.00952 0.00449 -0.1266 0.3976 1.0000
4.500 1.1866 0.00970 0.00463 -0.1261 0.3892 1.0000
4.750 1.2099 0.00995 0.00480 -0.1253 0.3797 1.0000
5.000 1.2340 0.01016 0.00497 -0.1247 0.3717 1.0000
5.250 1.2557 0.01044 0.00518 -0.1237 0.3628 1.0000
5.500 1.2776 0.01067 0.00537 -0.1226 0.3557 1.0000
5.750 1.2982 0.01096 0.00561 -0.1214 0.3484 1.0000
6.000 1.3191 0.01125 0.00586 -0.1202 0.3422 1.0000
6.250 1.3414 0.01150 0.00609 -0.1193 0.3370 1.0000
6.500 1.3619 0.01183 0.00638 -0.1182 0.3313 1.0000
6.750 1.3824 0.01216 0.00668 -0.1171 0.3262 1.0000
7.000 1.4051 0.01241 0.00693 -0.1164 0.3229 1.0000
7.250 1.4265 0.01272 0.00723 -0.1155 0.3189 1.0000
7.500 1.4464 0.01310 0.00758 -0.1144 0.3147 1.0000
7.750 1.4653 0.01352 0.00798 -0.1131 0.3102 1.0000
8.000 1.4881 0.01379 0.00826 -0.1125 0.3077 1.0000
8.250 1.5093 0.01412 0.00860 -0.1117 0.3046 1.0000
8.500 1.5292 0.01451 0.00900 -0.1108 0.3014 1.0000
8.750 1.5479 0.01498 0.00945 -0.1096 0.2978 1.0000
9.000 1.5648 0.01554 0.01000 -0.1083 0.2940 1.0000
9.250 1.5868 0.01586 0.01035 -0.1077 0.2920 1.0000
9.500 1.6074 0.01626 0.01076 -0.1070 0.2893 1.0000
9.750 1.6262 0.01674 0.01126 -0.1060 0.2862 1.0000
10.000 1.6436 0.01732 0.01183 -0.1050 0.2828 1.0000
10.250 1.6582 0.01806 0.01256 -0.1036 0.2788 1.0000
10.500 1.6779 0.01853 0.01307 -0.1028 0.2763 1.0000
10.750 1.6970 0.01905 0.01361 -0.1021 0.2732 1.0000
11.000 1.7136 0.01972 0.01429 -0.1011 0.2694 1.0000
11.250 1.7277 0.02056 0.01513 -0.0999 0.2653 1.0000
11.500 1.7423 0.02138 0.01597 -0.0987 0.2616 1.0000
11.750 1.7601 0.02202 0.01663 -0.0980 0.2582 1.0000
12.000 1.7742 0.02290 0.01754 -0.0969 0.2538 1.0000
12.250 1.7840 0.02410 0.01872 -0.0955 0.2483 1.0000
12.500 1.7987 0.02499 0.01964 -0.0946 0.2434 1.0000
12.750 1.8083 0.02625 0.02089 -0.0933 0.2365 1.0000
13.000 1.8170 0.02761 0.02224 -0.0920 0.2297 1.0000
13.250 1.8226 0.02925 0.02387 -0.0906 0.2216 1.0000
13.500 1.8284 0.03092 0.02554 -0.0892 0.2134 1.0000
13.750 1.8286 0.03308 0.02767 -0.0876 0.2048 1.0000
14.000 1.8301 0.03521 0.02980 -0.0862 0.1968 1.0000
14.250 1.8286 0.03767 0.03226 -0.0847 0.1898 1.0000
14.500 1.8276 0.04016 0.03476 -0.0834 0.1838 1.0000
14.750 1.8252 0.04281 0.03742 -0.0822 0.1789 1.0000
15.000 1.8267 0.04517 0.03982 -0.0813 0.1752 1.0000
15.250 1.8240 0.04801 0.04269 -0.0803 0.1718 1.0000
15.500 1.8183 0.05121 0.04592 -0.0793 0.1682 1.0000
15.750 1.8208 0.05358 0.04835 -0.0787 0.1662 1.0000
16.000 1.8221 0.05613 0.05095 -0.0781 0.1643 1.0000
16.250 1.8204 0.05903 0.05390 -0.0775 0.1623 1.0000
16.500 1.8166 0.06217 0.05709 -0.0769 0.1601 1.0000
16.750 1.8111 0.06551 0.06047 -0.0764 0.1580 1.0000
17.000 1.8037 0.06911 0.06412 -0.0759 0.1559 1.0000
17.250 1.8079 0.07142 0.06650 -0.0757 0.1547 1.0000
17.500 1.8085 0.07418 0.06933 -0.0755 0.1533 1.0000
17.750 1.8093 0.07688 0.07208 -0.0753 0.1518 1.0000
18.000 1.8056 0.08012 0.07538 -0.0751 0.1503 1.0000
18.250 1.8031 0.08320 0.07851 -0.0749 0.1487 1.0000
18.500 1.7951 0.08701 0.08236 -0.0749 0.1469 1.0000
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