S9000 (9%) (s9000-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 50,000 Max Cl/Cd: 37.89 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9000-il-50000-n5.txt Download as CSV file: xf-s9000-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4406 0.10205 0.09489 -0.0293 1.0000 0.0415
-9.000 -0.4353 0.09854 0.09143 -0.0290 1.0000 0.0407
-8.750 -0.4334 0.09490 0.08786 -0.0297 1.0000 0.0400
-8.500 -0.4330 0.09125 0.08428 -0.0307 1.0000 0.0393
-8.250 -0.4348 0.08748 0.08060 -0.0319 1.0000 0.0387
-8.000 -0.4393 0.08359 0.07682 -0.0332 1.0000 0.0382
-7.750 -0.4451 0.07971 0.07304 -0.0348 1.0000 0.0376
-7.500 -0.4486 0.07512 0.06853 -0.0377 1.0000 0.0369
-7.250 -0.4522 0.07029 0.06373 -0.0403 1.0000 0.0363
-7.000 -0.4547 0.06552 0.05893 -0.0424 1.0000 0.0357
-6.750 -0.4557 0.06073 0.05405 -0.0441 1.0000 0.0351
-6.500 -0.4540 0.05604 0.04918 -0.0453 1.0000 0.0349
-6.250 -0.4484 0.05172 0.04460 -0.0460 1.0000 0.0350
-6.000 -0.4392 0.04776 0.04034 -0.0464 1.0000 0.0358
-5.750 -0.4269 0.04399 0.03618 -0.0466 1.0000 0.0371
-5.500 -0.4115 0.04035 0.03199 -0.0465 1.0000 0.0386
-5.250 -0.3932 0.03701 0.02809 -0.0462 1.0000 0.0399
-5.000 -0.3725 0.03393 0.02440 -0.0456 1.0000 0.0411
-4.750 -0.3515 0.03128 0.02141 -0.0449 1.0000 0.0429
-4.500 -0.3309 0.02956 0.01954 -0.0442 1.0000 0.0478
-4.250 -0.3077 0.02772 0.01725 -0.0431 1.0000 0.0531
-4.000 -0.2861 0.02606 0.01554 -0.0421 1.0000 0.0595
-3.750 -0.2638 0.02466 0.01393 -0.0409 1.0000 0.0697
-3.500 -0.2418 0.02346 0.01268 -0.0399 1.0000 0.0848
-3.250 -0.2192 0.02236 0.01148 -0.0390 1.0000 0.1078
-3.000 -0.1959 0.02117 0.01051 -0.0387 1.0000 0.1513
-2.750 -0.1723 0.01992 0.00981 -0.0387 1.0000 0.2479
-2.500 -0.1506 0.01884 0.00948 -0.0383 1.0000 0.4050
-2.250 -0.1353 0.01808 0.00947 -0.0355 1.0000 0.5749
-2.000 -0.1266 0.01777 0.00962 -0.0306 1.0000 0.7289
-1.750 -0.1157 0.01759 0.00958 -0.0262 1.0000 0.8558
-1.500 -0.0689 0.01744 0.00915 -0.0301 0.9943 1.0000
-1.250 -0.0252 0.01774 0.00899 -0.0340 0.9838 1.0000
-1.000 0.0165 0.01799 0.00889 -0.0374 0.9723 1.0000
-0.750 0.0568 0.01822 0.00882 -0.0405 0.9602 1.0000
-0.500 0.0966 0.01842 0.00875 -0.0433 0.9477 1.0000
-0.250 0.1361 0.01859 0.00871 -0.0460 0.9348 1.0000
0.000 0.1754 0.01874 0.00869 -0.0485 0.9217 1.0000
0.250 0.2147 0.01886 0.00866 -0.0509 0.9084 1.0000
0.500 0.2541 0.01895 0.00864 -0.0531 0.8951 1.0000
0.750 0.2938 0.01901 0.00861 -0.0554 0.8818 1.0000
1.000 0.3316 0.01905 0.00859 -0.0571 0.8676 1.0000
1.250 0.3677 0.01907 0.00857 -0.0584 0.8523 1.0000
1.500 0.4030 0.01908 0.00856 -0.0594 0.8362 1.0000
1.750 0.4377 0.01907 0.00853 -0.0603 0.8195 1.0000
2.000 0.4719 0.01905 0.00850 -0.0609 0.8025 1.0000
2.250 0.5024 0.01910 0.00855 -0.0609 0.7831 1.0000
2.500 0.5326 0.01915 0.00862 -0.0608 0.7630 1.0000
2.750 0.5638 0.01917 0.00864 -0.0607 0.7429 1.0000
3.000 0.5914 0.01928 0.00876 -0.0601 0.7198 1.0000
3.250 0.6196 0.01939 0.00886 -0.0596 0.6968 1.0000
3.500 0.6476 0.01952 0.00903 -0.0589 0.6732 1.0000
3.750 0.6735 0.01973 0.00925 -0.0581 0.6476 1.0000
4.000 0.6994 0.01996 0.00948 -0.0572 0.6215 1.0000
4.250 0.7248 0.02022 0.00977 -0.0562 0.5945 1.0000
4.500 0.7496 0.02053 0.01007 -0.0552 0.5666 1.0000
4.750 0.7737 0.02089 0.01041 -0.0542 0.5379 1.0000
5.000 0.7974 0.02130 0.01082 -0.0531 0.5091 1.0000
5.250 0.8207 0.02176 0.01131 -0.0520 0.4803 1.0000
5.500 0.8434 0.02228 0.01182 -0.0509 0.4512 1.0000
5.750 0.8657 0.02285 0.01240 -0.0498 0.4221 1.0000
6.000 0.8872 0.02347 0.01301 -0.0487 0.3928 1.0000
6.250 0.9083 0.02416 0.01373 -0.0475 0.3637 1.0000
6.500 0.9287 0.02490 0.01448 -0.0463 0.3352 1.0000
6.750 0.9488 0.02572 0.01531 -0.0451 0.3080 1.0000
7.000 0.9684 0.02661 0.01620 -0.0439 0.2821 1.0000
7.250 0.9873 0.02757 0.01715 -0.0427 0.2576 1.0000
7.500 1.0058 0.02861 0.01831 -0.0415 0.2334 1.0000
7.750 1.0235 0.02973 0.01947 -0.0403 0.2106 1.0000
8.000 1.0404 0.03093 0.02069 -0.0390 0.1901 1.0000
8.250 1.0570 0.03222 0.02206 -0.0377 0.1709 1.0000
8.500 1.0734 0.03363 0.02357 -0.0364 0.1540 1.0000
8.750 1.0884 0.03510 0.02513 -0.0350 0.1385 1.0000
9.000 1.1043 0.03677 0.02697 -0.0337 0.1257 1.0000
9.250 1.1197 0.03858 0.02893 -0.0324 0.1146 1.0000
9.500 1.1322 0.04034 0.03079 -0.0310 0.1040 1.0000
9.750 1.1450 0.04224 0.03280 -0.0296 0.0952 1.0000
10.000 1.1555 0.04448 0.03537 -0.0280 0.0867 1.0000
10.250 1.1638 0.04655 0.03749 -0.0265 0.0797 1.0000
10.500 1.1695 0.04914 0.04046 -0.0247 0.0736 1.0000
10.750 1.1745 0.05125 0.04252 -0.0230 0.0684 1.0000
11.000 1.1704 0.05439 0.04616 -0.0209 0.0642 1.0000
11.250 1.1681 0.05747 0.04951 -0.0193 0.0609 1.0000
11.500 1.1687 0.06011 0.05218 -0.0182 0.0578 1.0000
11.750 1.1597 0.06398 0.05631 -0.0174 0.0559 1.0000
12.000 1.1433 0.06866 0.06137 -0.0175 0.0547 1.0000
12.250 1.1252 0.07398 0.06700 -0.0187 0.0539 1.0000
12.500 1.1046 0.08017 0.07344 -0.0211 0.0537 1.0000
12.750 1.0817 0.08739 0.08088 -0.0248 0.0539 1.0000
13.000 1.0571 0.09578 0.08944 -0.0298 0.0547 1.0000
13.250 1.0323 0.10519 0.09897 -0.0356 0.0556 1.0000
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Polar data table (+)
Polar graphs
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