S1210 12% (s1210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 500,000 Max Cl/Cd: 115.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1210-il-500000-n5.txt Download as CSV file: xf-s1210-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1210 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0743 0.10232 0.09989 -0.0749 0.9643 0.0123
-9.000 -0.0634 0.09876 0.09633 -0.0773 0.9608 0.0119
-8.750 -0.0654 0.09323 0.09082 -0.0793 0.9540 0.0106
-8.500 -0.0530 0.09076 0.08836 -0.0809 0.9486 0.0109
-8.250 -0.0460 0.08845 0.08607 -0.0816 0.9390 0.0128
-8.000 -0.0357 0.08536 0.08298 -0.0834 0.9315 0.0126
-7.500 -0.0138 0.07693 0.07454 -0.0900 0.9118 0.0114
-7.000 0.0235 0.02364 0.02008 -0.1777 0.8745 0.0106
-6.750 0.1059 0.02001 0.01600 -0.1952 0.8599 0.0110
-6.500 0.1774 0.01789 0.01348 -0.2073 0.8389 0.0116
-6.250 0.2436 0.01596 0.01105 -0.2176 0.8111 0.0120
-6.000 0.2918 0.01483 0.00951 -0.2230 0.7802 0.0122
-5.750 0.3290 0.01410 0.00847 -0.2256 0.7508 0.0125
-5.500 0.3630 0.01358 0.00768 -0.2273 0.7240 0.0128
-5.250 0.3957 0.01319 0.00705 -0.2287 0.6990 0.0131
-5.000 0.4279 0.01290 0.00655 -0.2298 0.6767 0.0133
-4.750 0.4648 0.01235 0.00585 -0.2322 0.6565 0.0138
-4.500 0.4993 0.01204 0.00540 -0.2339 0.6389 0.0142
-4.250 0.5332 0.01181 0.00503 -0.2354 0.6239 0.0147
-4.000 0.5661 0.01164 0.00475 -0.2366 0.6103 0.0155
-3.750 0.5991 0.01149 0.00447 -0.2377 0.5977 0.0163
-3.500 0.6322 0.01134 0.00420 -0.2389 0.5864 0.0168
-3.250 0.6657 0.01119 0.00393 -0.2401 0.5762 0.0175
-3.000 0.6979 0.01110 0.00374 -0.2410 0.5663 0.0187
-2.750 0.7293 0.01105 0.00360 -0.2417 0.5575 0.0203
-2.500 0.7606 0.01101 0.00349 -0.2424 0.5484 0.0242
-2.250 0.7965 0.01077 0.00334 -0.2443 0.5401 0.0763
-2.000 0.8345 0.01046 0.00334 -0.2469 0.5320 0.2138
-1.750 0.8635 0.01053 0.00340 -0.2470 0.5256 0.2389
-1.500 0.8920 0.01063 0.00346 -0.2469 0.5191 0.2538
-1.000 0.9492 0.01082 0.00358 -0.2469 0.5076 0.2725
-0.750 0.9779 0.01091 0.00363 -0.2470 0.5016 0.2775
-0.500 1.0061 0.01102 0.00368 -0.2469 0.4962 0.2808
-0.250 1.0348 0.01110 0.00373 -0.2469 0.4914 0.2845
0.000 1.0635 0.01119 0.00380 -0.2469 0.4866 0.2883
0.250 1.0918 0.01130 0.00388 -0.2469 0.4821 0.2922
0.500 1.1202 0.01140 0.00397 -0.2469 0.4778 0.2965
0.750 1.1486 0.01150 0.00406 -0.2469 0.4734 0.3009
1.000 1.1769 0.01161 0.00416 -0.2468 0.4692 0.3056
1.250 1.2048 0.01175 0.00429 -0.2468 0.4652 0.3112
1.500 1.2329 0.01186 0.00440 -0.2467 0.4614 0.3173
1.750 1.2611 0.01196 0.00453 -0.2467 0.4565 0.3240
2.000 1.2885 0.01212 0.00467 -0.2465 0.4502 0.3324
2.250 1.3161 0.01225 0.00481 -0.2463 0.4444 0.3408
2.500 1.3438 0.01238 0.00496 -0.2462 0.4393 0.3503
2.750 1.3713 0.01253 0.00513 -0.2461 0.4351 0.3603
3.000 1.3984 0.01270 0.00531 -0.2459 0.4309 0.3713
3.250 1.4261 0.01281 0.00548 -0.2458 0.4256 0.3839
3.500 1.4530 0.01298 0.00566 -0.2455 0.4190 0.3974
3.750 1.4799 0.01316 0.00587 -0.2453 0.4133 0.4121
4.000 1.5071 0.01330 0.00606 -0.2451 0.4064 0.4296
4.250 1.5331 0.01353 0.00629 -0.2447 0.3989 0.4493
4.500 1.5602 0.01367 0.00650 -0.2445 0.3915 0.4703
4.750 1.5863 0.01388 0.00676 -0.2441 0.3843 0.4921
5.000 1.6131 0.01405 0.00699 -0.2439 0.3769 0.5162
5.250 1.6390 0.01428 0.00726 -0.2435 0.3689 0.5423
5.500 1.6653 0.01448 0.00754 -0.2432 0.3599 0.5712
5.750 1.6906 0.01475 0.00785 -0.2427 0.3469 0.6051
6.000 1.7152 0.01509 0.00821 -0.2421 0.3288 0.6457
6.250 1.7385 0.01557 0.00867 -0.2413 0.3069 0.6939
6.500 1.7609 0.01610 0.00919 -0.2404 0.2847 0.7493
6.750 1.7810 0.01668 0.00978 -0.2389 0.2631 0.8253
7.000 1.7906 0.01707 0.01020 -0.2352 0.2467 1.0000
7.250 1.8095 0.01776 0.01081 -0.2336 0.2300 1.0000
7.750 1.8452 0.01910 0.01204 -0.2299 0.2024 1.0000
8.000 1.8623 0.01976 0.01268 -0.2280 0.1906 1.0000
8.250 1.8785 0.02047 0.01336 -0.2259 0.1791 1.0000
8.500 1.8940 0.02124 0.01410 -0.2237 0.1679 1.0000
8.750 1.9083 0.02209 0.01490 -0.2214 0.1563 1.0000
9.000 1.9231 0.02287 0.01569 -0.2192 0.1472 1.0000
9.250 1.9371 0.02372 0.01654 -0.2169 0.1400 1.0000
9.500 1.9512 0.02456 0.01740 -0.2146 0.1332 1.0000
9.750 1.9634 0.02553 0.01838 -0.2121 0.1273 1.0000
10.000 1.9760 0.02647 0.01935 -0.2097 0.1211 1.0000
10.250 1.9862 0.02760 0.02050 -0.2070 0.1156 1.0000
10.500 1.9978 0.02864 0.02160 -0.2046 0.1114 1.0000
10.750 2.0073 0.02986 0.02285 -0.2020 0.1062 1.0000
11.000 2.0144 0.03129 0.02430 -0.1992 0.1016 1.0000
11.250 2.0243 0.03251 0.02561 -0.1969 0.0984 1.0000
11.500 2.0317 0.03399 0.02713 -0.1944 0.0946 1.0000
11.750 2.0369 0.03570 0.02890 -0.1918 0.0912 1.0000
12.000 2.0423 0.03747 0.03074 -0.1894 0.0884 1.0000
12.250 2.0486 0.03921 0.03257 -0.1873 0.0855 1.0000
12.500 2.0522 0.04128 0.03470 -0.1851 0.0821 1.0000
12.750 2.0524 0.04382 0.03729 -0.1829 0.0784 1.0000
13.000 2.0551 0.04620 0.03975 -0.1811 0.0751 1.0000
13.250 2.0559 0.04894 0.04255 -0.1795 0.0707 1.0000
13.500 2.0542 0.05207 0.04574 -0.1781 0.0674 1.0000
13.750 2.0541 0.05519 0.04896 -0.1769 0.0643 1.0000
14.000 2.0537 0.05846 0.05232 -0.1760 0.0614 1.0000
14.250 2.0521 0.06199 0.05596 -0.1752 0.0594 1.0000
14.500 2.0479 0.06603 0.06007 -0.1747 0.0569 1.0000
14.750 2.0446 0.07002 0.06417 -0.1743 0.0543 1.0000
15.000 2.0381 0.07460 0.06882 -0.1741 0.0494 1.0000
15.250 2.0307 0.07943 0.07373 -0.1742 0.0460 1.0000
15.500 2.0187 0.08507 0.07940 -0.1745 0.0397 1.0000
15.750 2.0093 0.09035 0.08477 -0.1750 0.0357 1.0000
16.000 1.9931 0.09685 0.09130 -0.1758 0.0296 1.0000
16.250 1.9812 0.10274 0.09726 -0.1768 0.0259 1.0000
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Polar data table (+)
Polar graphs
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