S1223 (s1223-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S1223 (s1223-il) Reynolds number: 100,000 Max Cl/Cd: 59.16 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223-il-100000-n5.txt Download as CSV file: xf-s1223-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 0.0289 0.10370 0.09907 -0.0665 0.9166 0.0463
-6.250 0.0326 0.10179 0.09720 -0.0682 0.9041 0.0470
-6.000 0.0331 0.10022 0.09568 -0.0696 0.8903 0.0473
-5.750 0.0499 0.09631 0.09180 -0.0695 0.8800 0.0479
-5.500 0.0667 0.09311 0.08861 -0.0701 0.8696 0.0489
-5.000 0.0803 0.08867 0.08423 -0.0696 0.8373 0.0511
-4.750 0.0858 0.08647 0.08203 -0.0701 0.8198 0.0527
-4.500 0.0947 0.08399 0.07954 -0.0745 0.8008 0.0542
-4.250 0.1153 0.08020 0.07572 -0.0813 0.7816 0.0547
-4.000 0.1397 0.07650 0.07194 -0.0801 0.7637 0.0559
-3.750 0.1708 0.07279 0.06811 -0.0842 0.7423 0.0582
-3.500 0.2143 0.06795 0.06310 -0.1009 0.7163 0.0629
-3.250 0.2376 0.06512 0.06012 -0.0978 0.6911 0.0658
-3.000 0.2930 0.06000 0.05475 -0.1157 0.6651 0.0731
-2.500 0.3707 0.04916 0.04342 -0.1303 0.6235 0.0401
-2.000 0.7660 0.02393 0.01508 -0.2296 0.5690 0.0381
-1.750 0.8233 0.02281 0.01340 -0.2360 0.5536 0.0399
-1.500 0.8701 0.02226 0.01257 -0.2400 0.5408 0.0431
-1.250 0.9132 0.02198 0.01199 -0.2431 0.5293 0.0475
-1.000 0.9550 0.02173 0.01164 -0.2461 0.5186 0.0511
-0.750 0.9981 0.02166 0.01135 -0.2493 0.5091 0.0586
-0.500 1.0410 0.02155 0.01111 -0.2525 0.5003 0.0712
-0.250 1.0910 0.02132 0.01116 -0.2575 0.4922 0.1945
0.000 1.1230 0.02174 0.01149 -0.2582 0.4861 0.2726
0.250 1.1513 0.02219 0.01198 -0.2582 0.4795 0.3256
0.500 1.1821 0.02246 0.01211 -0.2586 0.4734 0.3424
1.000 1.2440 0.02300 0.01240 -0.2596 0.4623 0.3694
1.250 1.2738 0.02325 0.01260 -0.2599 0.4570 0.3821
1.500 1.3040 0.02355 0.01281 -0.2603 0.4525 0.3980
1.750 1.3349 0.02391 0.01303 -0.2608 0.4488 0.4159
2.000 1.3632 0.02419 0.01335 -0.2608 0.4443 0.4348
2.250 1.3914 0.02450 0.01368 -0.2608 0.4397 0.4574
2.500 1.4199 0.02483 0.01401 -0.2608 0.4355 0.4861
2.750 1.4488 0.02517 0.01435 -0.2610 0.4318 0.5195
3.000 1.4786 0.02556 0.01472 -0.2613 0.4287 0.5606
3.250 1.5053 0.02590 0.01522 -0.2610 0.4251 0.6108
3.500 1.5307 0.02621 0.01569 -0.2604 0.4214 0.6777
3.750 1.5513 0.02640 0.01605 -0.2587 0.4179 0.7765
4.000 1.5672 0.02649 0.01620 -0.2561 0.4149 1.0000
4.250 1.5962 0.02700 0.01660 -0.2563 0.4120 1.0000
4.500 1.6249 0.02756 0.01707 -0.2566 0.4093 1.0000
4.750 1.6501 0.02811 0.01767 -0.2561 0.4061 1.0000
5.000 1.6753 0.02867 0.01826 -0.2556 0.4027 1.0000
5.250 1.7006 0.02921 0.01883 -0.2552 0.3994 1.0000
5.500 1.7264 0.02975 0.01934 -0.2549 0.3964 1.0000
5.750 1.7532 0.03030 0.01985 -0.2547 0.3938 1.0000
6.000 1.7814 0.03090 0.02038 -0.2549 0.3915 1.0000
6.250 1.8022 0.03157 0.02123 -0.2536 0.3884 1.0000
6.500 1.8235 0.03224 0.02201 -0.2525 0.3851 1.0000
6.750 1.8455 0.03289 0.02273 -0.2515 0.3818 1.0000
7.000 1.8687 0.03350 0.02341 -0.2507 0.3789 1.0000
7.250 1.8931 0.03408 0.02400 -0.2502 0.3761 1.0000
7.500 1.9194 0.03466 0.02454 -0.2500 0.3735 1.0000
7.750 1.9355 0.03550 0.02557 -0.2480 0.3701 1.0000
8.000 1.9514 0.03631 0.02659 -0.2459 0.3665 1.0000
8.250 1.9695 0.03704 0.02743 -0.2442 0.3629 1.0000
8.500 1.9897 0.03767 0.02811 -0.2430 0.3596 1.0000
8.750 2.0130 0.03821 0.02866 -0.2422 0.3566 1.0000
9.000 2.0287 0.03904 0.02962 -0.2402 0.3533 1.0000
9.250 2.0350 0.04010 0.03094 -0.2366 0.3492 1.0000
9.500 2.0453 0.04099 0.03197 -0.2336 0.3454 1.0000
9.750 2.0603 0.04166 0.03274 -0.2315 0.3418 1.0000
10.000 2.0812 0.04218 0.03326 -0.2303 0.3387 1.0000
10.250 2.0861 0.04336 0.03465 -0.2267 0.3351 1.0000
10.500 2.0845 0.04481 0.03636 -0.2221 0.3308 1.0000
10.750 2.0906 0.04590 0.03762 -0.2187 0.3266 1.0000
11.000 2.1046 0.04655 0.03831 -0.2166 0.3227 1.0000
11.250 2.1132 0.04756 0.03942 -0.2138 0.3188 1.0000
11.500 2.1022 0.04979 0.04198 -0.2085 0.3141 1.0000
11.750 2.1014 0.05142 0.04380 -0.2048 0.3094 1.0000
12.000 2.1115 0.05232 0.04476 -0.2025 0.3052 1.0000
12.250 2.1066 0.05444 0.04708 -0.1987 0.3007 1.0000
12.500 2.0908 0.05759 0.05053 -0.1943 0.2955 1.0000
12.750 2.0889 0.05964 0.05272 -0.1914 0.2907 1.0000
13.000 2.0889 0.06158 0.05476 -0.1889 0.2859 1.0000
13.250 2.0589 0.06690 0.06044 -0.1852 0.2803 1.0000
13.500 2.0482 0.07041 0.06412 -0.1831 0.2749 1.0000
13.750 2.0375 0.07425 0.06810 -0.1815 0.2698 1.0000
14.000 1.9866 0.08410 0.07829 -0.1808 0.2635 1.0000
14.250 1.9828 0.08762 0.08190 -0.1804 0.2580 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S1223 (s1223-il)