S2055 (s2055-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 50,000 Max Cl/Cd: 35.12 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2055-il-50000.txt Download as CSV file: xf-s2055-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S2055
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4736 0.10208 0.09526 -0.0125 1.0000 0.2395
-8.250 -0.4870 0.10061 0.09392 -0.0133 1.0000 0.2506
-8.000 -0.4804 0.09709 0.09045 -0.0123 1.0000 0.2643
-7.750 -0.4610 0.09249 0.08581 -0.0100 1.0000 0.2854
-7.500 -0.4610 0.08988 0.08328 -0.0088 1.0000 0.3035
-7.250 -0.4737 0.08806 0.08160 -0.0076 1.0000 0.3206
-7.000 -0.4614 0.08452 0.07810 -0.0050 1.0000 0.3475
-6.750 -0.4503 0.08102 0.07463 -0.0027 1.0000 0.3714
-6.500 -0.4491 0.07828 0.07198 0.0001 1.0000 0.3969
-6.250 -0.4427 0.07543 0.06919 0.0030 1.0000 0.4260
-6.000 -0.4378 0.07281 0.06663 0.0065 1.0000 0.4591
-5.000 -0.4578 0.04611 0.03807 -0.0310 1.0000 0.1380
-4.750 -0.4387 0.04174 0.03314 -0.0303 1.0000 0.1238
-4.500 -0.4200 0.03808 0.02925 -0.0292 1.0000 0.1189
-4.250 -0.3990 0.03484 0.02544 -0.0281 1.0000 0.1157
-4.000 -0.3775 0.03238 0.02251 -0.0269 1.0000 0.1207
-3.750 -0.3536 0.02999 0.01953 -0.0256 1.0000 0.1235
-3.500 -0.3293 0.02761 0.01687 -0.0245 1.0000 0.1275
-3.250 -0.3056 0.02582 0.01490 -0.0233 1.0000 0.1418
-3.000 -0.2804 0.02404 0.01302 -0.0220 1.0000 0.1586
-2.750 -0.1510 0.01755 0.00993 -0.0319 1.0000 1.0000
-2.500 -0.1446 0.01737 0.00932 -0.0288 1.0000 1.0000
-2.250 -0.1372 0.01723 0.00883 -0.0258 1.0000 1.0000
-2.000 -0.1284 0.01715 0.00840 -0.0230 1.0000 1.0000
-1.750 -0.1181 0.01711 0.00806 -0.0204 1.0000 1.0000
-1.500 -0.1057 0.01711 0.00779 -0.0182 1.0000 1.0000
-1.250 -0.0916 0.01716 0.00757 -0.0163 1.0000 1.0000
-1.000 -0.0761 0.01724 0.00742 -0.0147 1.0000 1.0000
-0.750 -0.0594 0.01736 0.00731 -0.0132 1.0000 1.0000
-0.500 -0.0421 0.01751 0.00724 -0.0120 1.0000 1.0000
-0.250 -0.0241 0.01769 0.00725 -0.0109 1.0000 1.0000
0.000 -0.0058 0.01791 0.00731 -0.0099 1.0000 1.0000
0.250 0.0128 0.01815 0.00742 -0.0090 1.0000 1.0000
0.500 0.0317 0.01843 0.00756 -0.0081 1.0000 1.0000
0.750 0.0506 0.01874 0.00777 -0.0074 1.0000 1.0000
1.000 0.0695 0.01909 0.00805 -0.0067 1.0000 1.0000
1.250 0.0883 0.01947 0.00837 -0.0061 1.0000 1.0000
1.500 0.1070 0.01990 0.00876 -0.0055 1.0000 1.0000
1.750 0.1256 0.02037 0.00920 -0.0050 1.0000 1.0000
2.000 0.1439 0.02088 0.00971 -0.0046 1.0000 1.0000
2.250 0.1618 0.02146 0.01029 -0.0042 1.0000 1.0000
2.500 0.1793 0.02210 0.01095 -0.0039 1.0000 1.0000
2.750 0.1963 0.02281 0.01171 -0.0037 1.0000 1.0000
3.000 0.2264 0.02390 0.01290 -0.0062 0.9938 1.0000
3.250 0.3005 0.02554 0.01477 -0.0166 0.9619 1.0000
3.500 0.3742 0.02664 0.01618 -0.0258 0.9295 1.0000
3.750 0.4362 0.02706 0.01691 -0.0320 0.8944 1.0000
4.000 0.5120 0.02680 0.01709 -0.0392 0.8588 1.0000
4.250 0.5854 0.02570 0.01654 -0.0444 0.8188 1.0000
4.500 0.6478 0.02410 0.01539 -0.0462 0.7731 1.0000
4.750 0.6963 0.02255 0.01418 -0.0450 0.7163 1.0000
5.000 0.7310 0.02161 0.01325 -0.0420 0.6482 1.0000
5.250 0.7552 0.02155 0.01297 -0.0385 0.5758 1.0000
5.500 0.7757 0.02209 0.01316 -0.0354 0.5067 1.0000
5.750 0.7937 0.02304 0.01381 -0.0325 0.4416 1.0000
6.000 0.8099 0.02430 0.01477 -0.0297 0.3769 1.0000
6.250 0.8247 0.02591 0.01600 -0.0269 0.3084 1.0000
6.500 0.8409 0.02798 0.01756 -0.0245 0.2433 1.0000
6.750 0.8595 0.03018 0.01967 -0.0225 0.1966 1.0000
7.000 0.8790 0.03219 0.02160 -0.0209 0.1646 1.0000
7.250 0.9019 0.03481 0.02434 -0.0197 0.1446 1.0000
7.500 0.9213 0.03729 0.02710 -0.0182 0.1289 1.0000
7.750 0.9449 0.04066 0.03049 -0.0173 0.1203 1.0000
8.000 0.9569 0.04429 0.03496 -0.0149 0.1158 1.0000
8.250 0.9756 0.04740 0.03799 -0.0141 0.1071 1.0000
8.500 0.9804 0.05150 0.04283 -0.0115 0.1055 1.0000
8.750 0.9837 0.05610 0.04796 -0.0094 0.1054 1.0000
9.000 0.9838 0.06095 0.05324 -0.0075 0.1059 1.0000
9.250 0.9843 0.06607 0.05864 -0.0061 0.1068 1.0000
9.500 0.9472 0.07156 0.06480 -0.0041 0.1115 1.0000
9.750 0.9203 0.07701 0.07044 -0.0035 0.1146 1.0000
10.000 0.9001 0.08223 0.07573 -0.0036 0.1171 1.0000
10.250 0.8950 0.08781 0.08133 -0.0041 0.1195 1.0000
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Polar data table (+)
Polar graphs
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