S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 50,000 Max Cl/Cd: 27.07 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-il-50000.txt Download as CSV file: xf-s1221-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S1221 w/o flap
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2539 0.11445 0.10789 -0.0166 1.0000 0.2135
-7.250 -0.2475 0.11203 0.10555 -0.0161 1.0000 0.2215
-7.000 -0.2738 0.11430 0.10803 -0.0170 1.0000 0.2254
-6.750 -0.2374 0.10665 0.10036 -0.0153 1.0000 0.2330
-6.500 -0.2514 0.10696 0.10082 -0.0152 1.0000 0.2404
-6.250 -0.2397 0.10277 0.09671 -0.0145 1.0000 0.2443
-6.000 -0.2299 0.09975 0.09377 -0.0134 1.0000 0.2511
-5.750 -0.2559 0.10127 0.09551 -0.0122 1.0000 0.2572
-5.500 -0.2373 0.09624 0.09054 -0.0115 1.0000 0.2610
-5.250 -0.2301 0.09348 0.08788 -0.0101 1.0000 0.2672
-5.000 -0.2589 0.09477 0.08942 -0.0079 1.0000 0.2738
-4.750 -0.2546 0.09140 0.08618 -0.0066 1.0000 0.2766
-4.500 -0.2462 0.08835 0.08323 -0.0047 1.0000 0.2805
-4.250 -0.2509 0.08676 0.08182 -0.0031 1.0000 0.2858
-4.000 -0.2802 0.08779 0.08315 -0.0043 1.0000 0.2919
-3.750 -0.2854 0.08564 0.08116 -0.0009 1.0000 0.2932
-3.500 -0.3030 0.08534 0.08106 0.0026 1.0000 0.2944
-3.250 -0.1867 0.04851 0.04304 -0.0753 1.0000 0.1199
-3.000 -0.0716 0.03786 0.03125 -0.1006 0.9913 0.1128
-2.750 0.0376 0.03214 0.02422 -0.1187 0.9736 0.1187
-2.500 0.1167 0.02893 0.02082 -0.1281 0.9463 0.1310
-2.250 0.1938 0.02615 0.01829 -0.1367 0.9173 0.1716
-2.000 0.2497 0.02791 0.02125 -0.1363 0.8842 0.3953
-1.750 0.2742 0.02928 0.02286 -0.1289 0.8583 0.4704
-1.500 0.3063 0.02922 0.02264 -0.1255 0.8295 0.5215
-1.250 0.3519 0.02846 0.02150 -0.1269 0.8009 0.5540
-1.000 0.4026 0.02778 0.02033 -0.1307 0.7736 0.5774
-0.750 0.4415 0.02749 0.01970 -0.1326 0.7478 0.5928
-0.500 0.4806 0.02731 0.01917 -0.1347 0.7262 0.6060
-0.250 0.5196 0.02726 0.01882 -0.1372 0.7071 0.6186
0.000 0.5596 0.02732 0.01859 -0.1403 0.6896 0.6306
0.250 0.5888 0.02749 0.01864 -0.1408 0.6741 0.6410
0.500 0.6208 0.02773 0.01876 -0.1421 0.6597 0.6525
0.750 0.6554 0.02806 0.01894 -0.1442 0.6469 0.6650
1.000 0.6867 0.02839 0.01912 -0.1450 0.6366 0.6789
1.250 0.7136 0.02884 0.01955 -0.1453 0.6258 0.6933
1.500 0.7416 0.02933 0.02000 -0.1457 0.6163 0.7093
1.750 0.7698 0.02980 0.02042 -0.1460 0.6074 0.7286
2.000 0.7938 0.03046 0.02112 -0.1458 0.5996 0.7510
2.250 0.8158 0.03105 0.02176 -0.1450 0.5921 0.7773
2.500 0.8378 0.03151 0.02223 -0.1439 0.5858 0.8110
2.750 0.8479 0.03221 0.02316 -0.1414 0.5787 0.8529
3.000 0.8592 0.03215 0.02326 -0.1384 0.5731 1.0000
3.250 0.9238 0.03413 0.02499 -0.1494 0.5646 1.0000
3.500 0.9599 0.03566 0.02634 -0.1526 0.5575 1.0000
3.750 0.9924 0.03693 0.02742 -0.1540 0.5519 1.0000
4.000 1.0090 0.03934 0.02997 -0.1546 0.5456 1.0000
4.250 1.0327 0.04112 0.03171 -0.1551 0.5403 1.0000
4.500 1.0622 0.04239 0.03287 -0.1555 0.5355 1.0000
4.750 1.0648 0.04612 0.03683 -0.1555 0.5297 1.0000
5.000 1.0769 0.04905 0.03986 -0.1557 0.5248 1.0000
5.250 1.1028 0.05069 0.04147 -0.1559 0.5205 1.0000
5.500 1.1025 0.05498 0.04589 -0.1559 0.5163 1.0000
5.750 1.0720 0.06226 0.05337 -0.1561 0.5136 1.0000
6.000 1.0353 0.07003 0.06125 -0.1566 0.5145 1.0000
6.250 1.0131 0.07669 0.06795 -0.1577 0.5165 1.0000
6.500 1.0064 0.08222 0.07353 -0.1592 0.5196 1.0000
6.750 0.8163 0.10358 0.09525 -0.1712 0.6768 1.0000
7.000 0.8280 0.10643 0.09810 -0.1711 0.6622 1.0000
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Polar data table (+)
Polar graphs
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