S1223 (s1223-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 (s1223-il) Reynolds number: 50,000 Max Cl/Cd: 33.06 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223-il-50000.txt Download as CSV file: xf-s1223-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-4.250 -0.0828 0.11564 0.11083 -0.0447 0.9014 0.1609
-4.000 -0.0475 0.11002 0.10518 -0.0465 0.8871 0.1690
-3.750 -0.0409 0.11072 0.10591 -0.0538 0.8647 0.1762
-3.500 -0.0071 0.10406 0.09923 -0.0546 0.8541 0.1816
-3.250 0.0129 0.10130 0.09647 -0.0570 0.8379 0.1907
-3.000 0.0288 0.09977 0.09497 -0.0641 0.8207 0.1972
-2.750 0.0461 0.09568 0.09088 -0.0612 0.8071 0.2035
-2.500 0.0733 0.09527 0.09045 -0.0735 0.7904 0.2159
-2.250 0.0961 0.08932 0.08448 -0.0686 0.7834 0.2224
-2.000 0.1225 0.08867 0.08381 -0.0790 0.7675 0.2362
-1.750 0.1506 0.08297 0.07808 -0.0754 0.7629 0.2462
-1.500 0.1642 0.08205 0.07718 -0.0799 0.7474 0.2583
-1.250 0.1763 0.08012 0.07525 -0.0783 0.7365 0.2700
-1.000 0.2092 0.07659 0.07168 -0.0819 0.7280 0.2854
-0.750 0.2604 0.07211 0.06711 -0.0888 0.7225 0.3060
-0.500 0.2752 0.07178 0.06679 -0.0925 0.7092 0.3186
-0.250 0.3430 0.06612 0.06098 -0.1007 0.7058 0.3412
0.000 1.0370 0.03358 0.02536 -0.2494 0.6974 0.3628
0.250 1.0579 0.03407 0.02590 -0.2458 0.6878 0.4698
0.500 1.0660 0.03492 0.02683 -0.2413 0.6781 0.5138
0.750 1.1061 0.03496 0.02662 -0.2430 0.6690 0.5588
1.000 1.1377 0.03567 0.02717 -0.2444 0.6595 0.5859
1.250 1.1734 0.03607 0.02739 -0.2460 0.6508 0.6117
1.500 1.2120 0.03675 0.02786 -0.2485 0.6431 0.6377
1.750 1.2302 0.03803 0.02916 -0.2477 0.6354 0.6598
2.000 1.2700 0.03842 0.02938 -0.2499 0.6290 0.6930
2.250 1.2815 0.03995 0.03101 -0.2478 0.6225 0.7201
2.500 1.2896 0.04167 0.03285 -0.2454 0.6157 0.7528
2.750 1.3134 0.04213 0.03333 -0.2446 0.6105 0.8101
3.000 1.3201 0.04244 0.03376 -0.2407 0.6067 0.9341
3.250 1.2851 0.04798 0.03967 -0.2347 0.5998 1.0000
3.500 1.3406 0.05048 0.04176 -0.2427 0.5928 1.0000
3.750 1.4128 0.04999 0.04075 -0.2493 0.5882 1.0000
4.000 1.1095 0.07727 0.06975 -0.2200 0.5846 0.8296
4.250 1.0692 0.08693 0.07957 -0.2200 0.5843 0.8182
4.500 1.0523 0.09182 0.08467 -0.2186 0.5853 0.8746
4.750 1.0753 0.09731 0.08997 -0.2242 0.5868 1.0000
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Polar data table (+)
Polar graphs
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