S1223 (s1223-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 50,000 Max Cl/Cd: 42.3 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223-il-50000-n5.txt Download as CSV file: xf-s1223-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1223
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
------ -------- --------- --------- -------- -------- --------
-6.250 -0.0584 0.11731 0.11139 -0.0461 0.9503 0.0921
-6.000 -0.0522 0.11606 0.11019 -0.0494 0.9358 0.0956
-5.750 -0.0572 0.11654 0.11075 -0.0527 0.9183 0.0967
-5.500 -0.0189 0.10881 0.10303 -0.0535 0.9117 0.0999
-5.250 -0.0009 0.10560 0.09984 -0.0553 0.8989 0.1035
-5.000 0.0071 0.10344 0.09772 -0.0564 0.8826 0.1071
-4.750 0.0032 0.10309 0.09744 -0.0585 0.8612 0.1103
-4.500 0.0129 0.10092 0.09534 -0.0629 0.8427 0.1115
-4.250 0.0402 0.09527 0.08967 -0.0613 0.8344 0.1143
-4.000 0.0561 0.09212 0.08653 -0.0619 0.8183 0.1180
-3.750 0.0695 0.08961 0.08404 -0.0644 0.8007 0.1234
-3.250 0.1040 0.08331 0.07774 -0.0709 0.7666 0.1289
-3.000 0.1248 0.07994 0.07434 -0.0717 0.7512 0.1320
-2.500 0.2103 0.06721 0.06122 -0.0959 0.7248 0.0719
-2.000 0.3303 0.05482 0.04838 -0.1236 0.6949 0.0628
-1.750 0.3927 0.04998 0.04329 -0.1346 0.6803 0.0612
-1.500 0.6753 0.03305 0.02413 -0.2027 0.6594 0.0628
-1.250 0.7522 0.03077 0.02118 -0.2134 0.6409 0.0663
-1.000 0.8185 0.02945 0.01914 -0.2213 0.6240 0.0739
-0.750 0.8728 0.02878 0.01803 -0.2265 0.6087 0.0824
-0.500 0.9240 0.02838 0.01736 -0.2312 0.5946 0.0976
-0.250 0.9815 0.02802 0.01703 -0.2374 0.5825 0.1449
0.000 1.0242 0.02857 0.01774 -0.2402 0.5714 0.2877
0.250 1.0544 0.02934 0.01854 -0.2402 0.5620 0.3631
0.500 1.0896 0.02968 0.01865 -0.2414 0.5527 0.3969
0.750 1.1271 0.02994 0.01863 -0.2431 0.5448 0.4189
1.000 1.1608 0.03026 0.01879 -0.2443 0.5366 0.4373
1.250 1.1982 0.03056 0.01886 -0.2460 0.5300 0.4579
1.500 1.2315 0.03095 0.01913 -0.2471 0.5236 0.4781
1.750 1.2623 0.03138 0.01951 -0.2477 0.5168 0.5010
2.000 1.2961 0.03177 0.01980 -0.2488 0.5110 0.5292
2.250 1.3280 0.03221 0.02019 -0.2496 0.5056 0.5608
2.500 1.3538 0.03274 0.02084 -0.2492 0.4997 0.5980
2.750 1.3811 0.03320 0.02139 -0.2491 0.4947 0.6465
3.000 1.4073 0.03352 0.02178 -0.2485 0.4905 0.7171
3.250 1.4206 0.03358 0.02198 -0.2453 0.4868 0.8638
3.500 1.4447 0.03441 0.02281 -0.2450 0.4814 1.0000
3.750 1.4729 0.03530 0.02358 -0.2454 0.4764 1.0000
4.000 1.5029 0.03611 0.02425 -0.2460 0.4722 1.0000
4.250 1.5355 0.03687 0.02482 -0.2470 0.4687 1.0000
4.500 1.5556 0.03799 0.02604 -0.2460 0.4643 1.0000
4.750 1.5758 0.03910 0.02721 -0.2449 0.4597 1.0000
5.000 1.5992 0.04009 0.02820 -0.2444 0.4555 1.0000
5.250 1.6259 0.04099 0.02903 -0.2443 0.4519 1.0000
5.500 1.6559 0.04182 0.02979 -0.2448 0.4489 1.0000
5.750 1.6669 0.04335 0.03153 -0.2423 0.4447 1.0000
6.000 1.6794 0.04484 0.03318 -0.2402 0.4403 1.0000
6.250 1.6972 0.04610 0.03451 -0.2388 0.4363 1.0000
6.500 1.7201 0.04716 0.03558 -0.2382 0.4330 1.0000
6.750 1.7486 0.04801 0.03643 -0.2384 0.4301 1.0000
7.000 1.7518 0.05004 0.03870 -0.2350 0.4261 1.0000
7.250 1.7487 0.05239 0.04131 -0.2307 0.4216 1.0000
7.500 1.7554 0.05422 0.04330 -0.2279 0.4175 1.0000
7.750 1.7735 0.05548 0.04462 -0.2267 0.4140 1.0000
8.000 1.8040 0.05615 0.04530 -0.2271 0.4110 1.0000
8.250 1.7699 0.06015 0.04966 -0.2191 0.4064 1.0000
8.500 1.7174 0.06578 0.05567 -0.2101 0.4009 1.0000
8.750 1.7083 0.06905 0.05909 -0.2065 0.3965 1.0000
9.000 1.7381 0.06940 0.05945 -0.2065 0.3935 1.0000
9.500 1.5208 0.10105 0.09186 -0.1979 0.3713 1.0000
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Polar data table (+)
Polar graphs
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