S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 100,000 Max Cl/Cd: 49.79 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1223rtl-il-100000-n5.txt Download as CSV file: xf-s1223rtl-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 0.0250 0.10678 0.10224 -0.0674 0.9107 0.0490
-7.000 0.0329 0.10428 0.09977 -0.0707 0.9028 0.0498
-6.750 0.0301 0.10271 0.09825 -0.0713 0.8911 0.0500
-6.500 0.0477 0.09875 0.09432 -0.0710 0.8811 0.0506
-6.250 0.0653 0.09546 0.09104 -0.0717 0.8708 0.0518
-6.000 0.0713 0.09322 0.08883 -0.0711 0.8556 0.0533
-5.750 0.0719 0.09143 0.08708 -0.0712 0.8399 0.0561
-5.500 0.0682 0.08982 0.08550 -0.0714 0.8222 0.0568
-5.250 0.0827 0.08637 0.08205 -0.0716 0.8008 0.0586
-5.000 0.0998 0.08341 0.07902 -0.0725 0.7670 0.0607
-4.500 0.1914 0.07235 0.06661 -0.0955 0.5499 0.0665
-4.250 0.1989 0.07067 0.06462 -0.0942 0.5088 0.0674
-4.000 0.2074 0.06876 0.06255 -0.0943 0.4873 0.0682
-3.500 0.2436 0.05725 0.05079 -0.1085 0.4685 0.0380
-3.250 0.2671 0.05455 0.04796 -0.1120 0.4569 0.0372
-3.000 0.3089 0.04954 0.04279 -0.1224 0.4470 0.0361
-2.750 0.6024 0.02704 0.01744 -0.2044 0.4267 0.0382
-2.500 0.6493 0.02611 0.01618 -0.2090 0.4192 0.0400
-2.250 0.6981 0.02520 0.01482 -0.2136 0.4118 0.0439
-2.000 0.7388 0.02466 0.01411 -0.2165 0.4053 0.0465
-1.500 0.8200 0.02404 0.01311 -0.2217 0.3946 0.0558
-1.250 0.8602 0.02384 0.01282 -0.2243 0.3897 0.0620
-1.000 0.9015 0.02376 0.01258 -0.2271 0.3853 0.0741
-0.750 0.9481 0.02362 0.01237 -0.2313 0.3810 0.1038
-0.500 0.9921 0.02355 0.01261 -0.2350 0.3768 0.2395
-0.250 1.0231 0.02386 0.01294 -0.2355 0.3727 0.3004
0.000 1.0521 0.02428 0.01334 -0.2356 0.3689 0.3461
0.250 1.0815 0.02470 0.01364 -0.2357 0.3656 0.3787
0.500 1.1123 0.02506 0.01385 -0.2362 0.3627 0.3972
0.750 1.1443 0.02548 0.01411 -0.2369 0.3601 0.4117
1.000 1.1738 0.02577 0.01439 -0.2371 0.3573 0.4261
1.250 1.2031 0.02609 0.01467 -0.2373 0.3543 0.4411
1.500 1.2322 0.02644 0.01496 -0.2375 0.3511 0.4569
1.750 1.2607 0.02679 0.01526 -0.2376 0.3481 0.4729
2.000 1.2889 0.02716 0.01556 -0.2375 0.3454 0.4884
2.250 1.3174 0.02756 0.01587 -0.2376 0.3431 0.5050
2.500 1.3472 0.02805 0.01625 -0.2380 0.3410 0.5229
2.750 1.3741 0.02846 0.01671 -0.2378 0.3388 0.5405
3.000 1.4005 0.02888 0.01719 -0.2375 0.3364 0.5592
3.250 1.4268 0.02931 0.01767 -0.2372 0.3339 0.5789
3.500 1.4528 0.02975 0.01813 -0.2368 0.3313 0.6005
3.750 1.4787 0.03017 0.01858 -0.2364 0.3289 0.6236
4.000 1.5047 0.03058 0.01901 -0.2361 0.3267 0.6500
4.250 1.5309 0.03100 0.01946 -0.2358 0.3247 0.6830
4.500 1.5568 0.03143 0.01993 -0.2355 0.3230 0.7313
4.750 1.5723 0.03158 0.02029 -0.2329 0.3215 1.0000
5.000 1.5967 0.03226 0.02103 -0.2324 0.3194 1.0000
5.250 1.6208 0.03295 0.02179 -0.2319 0.3173 1.0000
5.500 1.6444 0.03363 0.02251 -0.2313 0.3150 1.0000
5.750 1.6678 0.03430 0.02320 -0.2306 0.3128 1.0000
6.000 1.6914 0.03495 0.02385 -0.2300 0.3106 1.0000
6.250 1.7153 0.03559 0.02449 -0.2294 0.3087 1.0000
6.500 1.7397 0.03624 0.02512 -0.2290 0.3070 1.0000
6.750 1.7651 0.03694 0.02578 -0.2288 0.3056 1.0000
7.000 1.7918 0.03772 0.02652 -0.2288 0.3042 1.0000
7.250 1.8089 0.03868 0.02767 -0.2271 0.3024 1.0000
7.500 1.8252 0.03969 0.02886 -0.2254 0.3004 1.0000
7.750 1.8414 0.04067 0.03001 -0.2236 0.2983 1.0000
8.000 1.8577 0.04162 0.03111 -0.2218 0.2961 1.0000
8.250 1.8744 0.04253 0.03212 -0.2202 0.2942 1.0000
8.500 1.8917 0.04343 0.03311 -0.2187 0.2925 1.0000
8.750 1.9100 0.04433 0.03409 -0.2173 0.2910 1.0000
9.000 1.9294 0.04520 0.03502 -0.2162 0.2896 1.0000
9.250 1.9503 0.04607 0.03592 -0.2153 0.2884 1.0000
9.500 1.9734 0.04695 0.03682 -0.2149 0.2872 1.0000
9.750 1.9768 0.04848 0.03860 -0.2113 0.2856 1.0000
10.000 1.9694 0.05036 0.04079 -0.2061 0.2835 1.0000
10.250 1.9641 0.05230 0.04300 -0.2015 0.2815 1.0000
10.500 1.9610 0.05425 0.04518 -0.1975 0.2796 1.0000
10.750 1.9595 0.05620 0.04733 -0.1938 0.2778 1.0000
11.000 1.9595 0.05817 0.04949 -0.1906 0.2763 1.0000
11.250 1.9610 0.06011 0.05158 -0.1877 0.2749 1.0000
11.500 1.9650 0.06192 0.05352 -0.1852 0.2736 1.0000
11.750 1.9716 0.06362 0.05533 -0.1831 0.2725 1.0000
12.000 1.9848 0.06491 0.05670 -0.1818 0.2714 1.0000
12.250 1.9844 0.06726 0.05920 -0.1793 0.2700 1.0000
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Polar data table (+)
Polar graphs
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