S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 50,000 Max Cl/Cd: 31.57 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223rtl-il-50000.txt Download as CSV file: xf-s1223rtl-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S1223 RTL
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
------ -------- --------- --------- -------- -------- --------
-6.000 -0.2273 0.13180 0.12702 -0.0060 1.0000 0.1440
-5.750 -0.2488 0.13347 0.12885 -0.0046 1.0000 0.1448
-5.500 -0.2707 0.13495 0.13050 -0.0029 1.0000 0.1451
-5.250 -0.2302 0.12541 0.12104 -0.0018 1.0000 0.1504
-5.000 -0.1950 0.12324 0.11888 -0.0114 0.9841 0.1599
-4.750 -0.1536 0.11823 0.11389 -0.0203 0.9641 0.1660
-4.500 -0.1147 0.11446 0.11013 -0.0285 0.9407 0.1774
-4.250 -0.0702 0.10846 0.10415 -0.0363 0.9173 0.1852
-4.000 -0.0389 0.10696 0.10267 -0.0494 0.8817 0.1982
-3.750 0.0137 0.09783 0.09354 -0.0495 0.8584 0.2101
-3.500 0.0482 0.09287 0.08859 -0.0554 0.8259 0.2225
-3.250 0.0852 0.08869 0.08437 -0.0637 0.7957 0.2386
-3.000 0.1274 0.08488 0.08048 -0.0726 0.7675 0.2571
-2.750 0.1617 0.07757 0.07309 -0.0683 0.7478 0.2664
-2.500 0.2002 0.07324 0.06860 -0.0743 0.7237 0.2822
-2.250 0.2420 0.06932 0.06448 -0.0810 0.6993 0.3005
-2.000 0.2872 0.06514 0.06004 -0.0864 0.6777 0.3215
-1.750 0.3305 0.06150 0.05611 -0.0914 0.6580 0.3429
-1.500 0.7183 0.03559 0.02752 -0.2026 0.6183 0.1585
-1.250 0.8342 0.03208 0.02278 -0.2224 0.5976 0.1774
-1.000 0.8898 0.03142 0.02188 -0.2280 0.5833 0.2067
-0.750 0.9403 0.03141 0.02180 -0.2320 0.5722 0.2712
-0.500 0.9664 0.03230 0.02294 -0.2296 0.5639 0.3802
-0.250 0.9815 0.03329 0.02397 -0.2249 0.5574 0.4589
0.000 0.9949 0.03395 0.02470 -0.2209 0.5505 0.5144
0.250 1.0178 0.03436 0.02498 -0.2189 0.5438 0.5634
0.500 1.0499 0.03479 0.02522 -0.2196 0.5373 0.6010
0.750 1.0774 0.03526 0.02565 -0.2199 0.5309 0.6274
1.000 1.1148 0.03582 0.02600 -0.2222 0.5252 0.6547
1.250 1.1523 0.03650 0.02641 -0.2244 0.5202 0.6807
1.500 1.1735 0.03734 0.02735 -0.2239 0.5153 0.7028
1.750 1.2008 0.03824 0.02823 -0.2246 0.5100 0.7291
2.000 1.2270 0.03898 0.02890 -0.2245 0.5053 0.7567
2.250 1.2568 0.03984 0.02962 -0.2251 0.5012 0.7911
2.500 1.2676 0.04102 0.03101 -0.2228 0.4982 0.8225
2.750 1.2727 0.04220 0.03245 -0.2195 0.4953 0.8620
3.000 1.2770 0.04339 0.03389 -0.2163 0.4923 1.0000
3.250 1.3202 0.04575 0.03611 -0.2216 0.4875 1.0000
3.500 1.3699 0.04767 0.03770 -0.2271 0.4829 1.0000
3.750 1.3970 0.05014 0.04005 -0.2286 0.4797 1.0000
4.000 1.3944 0.05346 0.04360 -0.2258 0.4777 1.0000
4.250 1.3795 0.05764 0.04804 -0.2217 0.4764 1.0000
4.500 1.3368 0.06377 0.05453 -0.2151 0.4760 1.0000
4.750 1.2342 0.07517 0.06647 -0.2052 0.4787 1.0000
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Polar data table (+)
Polar graphs
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