E221 (9.39%) (e221-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 200,000 Max Cl/Cd: 64.63 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e221-il-200000.txt Download as CSV file: xf-e221-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E221 (9.39%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4418 0.10954 0.10637 0.0007 1.0000 0.0447
-10.000 -0.4469 0.10518 0.10204 -0.0026 1.0000 0.0451
-8.250 -0.5272 0.08203 0.07885 -0.0107 1.0000 0.0487
-8.000 -0.5287 0.07831 0.07517 -0.0131 1.0000 0.0499
-7.750 -0.5333 0.07411 0.07098 -0.0160 1.0000 0.0514
-7.500 -0.5348 0.06920 0.06605 -0.0196 1.0000 0.0529
-6.750 -0.5348 0.05311 0.04941 -0.0263 1.0000 0.0596
-6.500 -0.5209 0.05041 0.04673 -0.0258 1.0000 0.0614
-6.250 -0.5083 0.04743 0.04363 -0.0254 1.0000 0.0644
-5.250 -0.4664 0.02677 0.02079 -0.0161 1.0000 0.0327
-5.000 -0.4585 0.02429 0.01802 -0.0128 1.0000 0.0310
-4.750 -0.4303 0.02134 0.01455 -0.0129 0.9945 0.0295
-4.500 -0.3885 0.01896 0.01179 -0.0153 0.9860 0.0295
-4.250 -0.3464 0.01743 0.01008 -0.0180 0.9766 0.0315
-4.000 -0.3050 0.01644 0.00893 -0.0204 0.9651 0.0347
-3.750 -0.2695 0.01457 0.00706 -0.0219 0.9516 0.0384
-3.500 -0.2352 0.01371 0.00611 -0.0228 0.9356 0.0453
-3.250 -0.2089 0.01230 0.00497 -0.0223 0.9181 0.0974
-3.000 -0.1867 0.01128 0.00453 -0.0212 0.9006 0.2239
-2.750 -0.1687 0.01040 0.00431 -0.0194 0.8830 0.3870
-2.500 -0.1531 0.00961 0.00416 -0.0167 0.8662 0.5551
-2.250 -0.1361 0.00890 0.00411 -0.0135 0.8512 0.7312
-2.000 -0.0647 0.00883 0.00428 -0.0204 0.8417 0.9124
-1.750 -0.0166 0.00915 0.00439 -0.0236 0.8281 0.9557
-1.500 0.0404 0.00934 0.00435 -0.0291 0.8144 0.9802
-1.250 0.1029 0.00928 0.00405 -0.0361 0.8003 0.9988
-1.000 0.1277 0.00927 0.00386 -0.0356 0.7854 1.0000
-0.750 0.1500 0.00927 0.00372 -0.0346 0.7710 1.0000
-0.500 0.1728 0.00929 0.00360 -0.0336 0.7570 1.0000
-0.250 0.1961 0.00932 0.00350 -0.0327 0.7433 1.0000
0.000 0.2197 0.00936 0.00342 -0.0318 0.7300 1.0000
0.250 0.2436 0.00940 0.00336 -0.0310 0.7168 1.0000
0.500 0.2678 0.00945 0.00331 -0.0302 0.7040 1.0000
0.750 0.2920 0.00951 0.00327 -0.0294 0.6913 1.0000
1.000 0.3163 0.00959 0.00325 -0.0286 0.6787 1.0000
1.250 0.3408 0.00967 0.00324 -0.0278 0.6665 1.0000
1.500 0.3655 0.00974 0.00325 -0.0271 0.6532 1.0000
1.750 0.3901 0.00982 0.00328 -0.0264 0.6400 1.0000
2.000 0.4149 0.00991 0.00333 -0.0258 0.6269 1.0000
2.250 0.4397 0.01001 0.00339 -0.0251 0.6137 1.0000
2.500 0.4645 0.01011 0.00345 -0.0244 0.6004 1.0000
2.750 0.4893 0.01022 0.00352 -0.0237 0.5870 1.0000
3.000 0.5141 0.01034 0.00359 -0.0230 0.5734 1.0000
3.250 0.5389 0.01046 0.00370 -0.0223 0.5595 1.0000
3.500 0.5636 0.01059 0.00381 -0.0216 0.5452 1.0000
3.750 0.5884 0.01073 0.00393 -0.0209 0.5307 1.0000
4.000 0.6130 0.01088 0.00408 -0.0203 0.5157 1.0000
4.250 0.6376 0.01103 0.00423 -0.0195 0.5001 1.0000
4.500 0.6621 0.01119 0.00439 -0.0188 0.4841 1.0000
4.750 0.6864 0.01137 0.00456 -0.0181 0.4673 1.0000
5.000 0.7105 0.01157 0.00475 -0.0173 0.4501 1.0000
5.250 0.7345 0.01177 0.00498 -0.0166 0.4314 1.0000
5.500 0.7584 0.01199 0.00521 -0.0158 0.4113 1.0000
5.750 0.7817 0.01225 0.00544 -0.0150 0.3902 1.0000
6.000 0.8050 0.01251 0.00573 -0.0142 0.3664 1.0000
6.250 0.8279 0.01281 0.00604 -0.0133 0.3418 1.0000
6.500 0.8503 0.01318 0.00638 -0.0124 0.3148 1.0000
6.750 0.8719 0.01361 0.00675 -0.0114 0.2834 1.0000
7.000 0.8924 0.01416 0.00720 -0.0104 0.2487 1.0000
7.250 0.9124 0.01478 0.00771 -0.0094 0.2109 1.0000
7.500 0.9316 0.01550 0.00830 -0.0083 0.1759 1.0000
7.750 0.9505 0.01626 0.00896 -0.0071 0.1451 1.0000
8.000 0.9683 0.01712 0.00972 -0.0059 0.1157 1.0000
8.250 0.9835 0.01829 0.01075 -0.0043 0.0809 1.0000
8.500 0.9921 0.02015 0.01235 -0.0019 0.0512 1.0000
8.750 1.0047 0.02147 0.01370 0.0001 0.0416 1.0000
9.000 1.0154 0.02294 0.01524 0.0024 0.0375 1.0000
9.250 1.0282 0.02418 0.01657 0.0043 0.0347 1.0000
9.500 1.0397 0.02552 0.01797 0.0063 0.0327 1.0000
9.750 1.0492 0.02728 0.01975 0.0084 0.0312 1.0000
10.000 1.0608 0.02950 0.02204 0.0103 0.0300 1.0000
10.250 1.0748 0.03080 0.02355 0.0119 0.0287 1.0000
10.500 1.0879 0.03235 0.02526 0.0135 0.0275 1.0000
10.750 1.0999 0.03417 0.02725 0.0152 0.0266 1.0000
11.000 1.1098 0.03620 0.02948 0.0169 0.0261 1.0000
11.250 1.1162 0.03834 0.03182 0.0189 0.0256 1.0000
11.500 1.1198 0.04071 0.03441 0.0209 0.0252 1.0000
11.750 1.1202 0.04327 0.03721 0.0227 0.0250 1.0000
12.000 1.1164 0.04627 0.04046 0.0243 0.0249 1.0000
12.250 1.1102 0.04940 0.04384 0.0254 0.0249 1.0000
12.500 1.1017 0.05268 0.04732 0.0259 0.0246 1.0000
12.750 1.0854 0.05712 0.05208 0.0257 0.0251 1.0000
13.000 1.0760 0.06082 0.05593 0.0249 0.0246 1.0000
13.250 1.0505 0.06691 0.06232 0.0225 0.0251 1.0000
13.500 1.0225 0.07398 0.06968 0.0188 0.0257 1.0000
13.750 0.9932 0.08205 0.07798 0.0140 0.0265 1.0000
14.000 0.9720 0.08927 0.08535 0.0092 0.0261 1.0000
14.250 0.9353 0.10068 0.09695 0.0017 0.0274 1.0000
14.500 0.9030 0.11257 0.10896 -0.0061 0.0281 1.0000
14.750 0.8650 0.12768 0.12412 -0.0152 0.0291 1.0000
15.000 0.8426 0.13906 0.13547 -0.0205 0.0300 1.0000
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Polar data table (+)
Polar graphs
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