E221 (9.39%) (e221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.93 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e221-il-1000000.txt Download as CSV file: xf-e221-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5444 0.08103 0.07953 -0.0074 1.0000 0.0100
-8.750 -0.5488 0.07591 0.07442 -0.0107 1.0000 0.0100
-8.500 -0.5609 0.06924 0.06779 -0.0166 1.0000 0.0100
-8.250 -0.5758 0.06196 0.06047 -0.0215 1.0000 0.0100
-8.000 -0.5846 0.05348 0.05184 -0.0247 1.0000 0.0100
-7.750 -0.5949 0.04622 0.04430 -0.0254 1.0000 0.0100
-7.500 -0.5958 0.02334 0.02109 -0.0243 1.0000 0.0103
-7.250 -0.5881 0.02003 0.01762 -0.0235 1.0000 0.0106
-7.000 -0.5725 0.01819 0.01569 -0.0229 1.0000 0.0109
-6.750 -0.5500 0.01521 0.01248 -0.0239 0.9664 0.0113
-6.500 -0.5713 0.02084 0.01700 -0.0186 0.9870 0.0092
-6.250 -0.5417 0.01805 0.01381 -0.0194 0.9608 0.0091
-6.000 -0.5205 0.01597 0.01134 -0.0180 0.9204 0.0088
-5.750 -0.5005 0.01471 0.00979 -0.0161 0.8871 0.0087
-5.500 -0.4777 0.01385 0.00871 -0.0149 0.8618 0.0089
-5.250 -0.4539 0.01307 0.00773 -0.0140 0.8410 0.0091
-5.000 -0.4296 0.01229 0.00679 -0.0131 0.8225 0.0092
-4.750 -0.4054 0.01150 0.00584 -0.0122 0.8060 0.0092
-4.500 -0.3808 0.01084 0.00505 -0.0114 0.7906 0.0093
-4.250 -0.3555 0.01033 0.00442 -0.0107 0.7764 0.0096
-4.000 -0.3293 0.01000 0.00399 -0.0102 0.7630 0.0100
-3.750 -0.3046 0.00934 0.00318 -0.0095 0.7505 0.0109
-3.500 -0.2783 0.00904 0.00281 -0.0090 0.7385 0.0119
-3.250 -0.2514 0.00881 0.00251 -0.0087 0.7266 0.0131
-3.000 -0.2245 0.00856 0.00219 -0.0083 0.7153 0.0152
-2.750 -0.1984 0.00819 0.00188 -0.0079 0.7044 0.0365
-2.500 -0.1726 0.00784 0.00168 -0.0075 0.6939 0.0821
-2.250 -0.1462 0.00757 0.00153 -0.0072 0.6831 0.1242
-2.000 -0.1199 0.00728 0.00140 -0.0069 0.6727 0.1772
-1.750 -0.0942 0.00695 0.00128 -0.0066 0.6626 0.2522
-1.500 -0.0693 0.00653 0.00118 -0.0061 0.6523 0.3555
-1.250 -0.0445 0.00612 0.00110 -0.0056 0.6420 0.4630
-1.000 -0.0199 0.00577 0.00103 -0.0050 0.6321 0.5644
-0.750 0.0026 0.00534 0.00098 -0.0039 0.6219 0.6863
-0.500 0.0235 0.00490 0.00095 -0.0022 0.6116 0.8125
-0.250 0.0555 0.00470 0.00105 -0.0026 0.6010 0.9229
0.000 0.0945 0.00484 0.00114 -0.0047 0.5895 0.9552
0.250 0.1265 0.00498 0.00121 -0.0054 0.5782 0.9695
0.500 0.1680 0.00510 0.00126 -0.0083 0.5659 0.9750
0.750 0.2069 0.00522 0.00130 -0.0105 0.5534 0.9807
1.000 0.2437 0.00532 0.00134 -0.0124 0.5406 0.9851
1.250 0.2856 0.00540 0.00135 -0.0155 0.5273 0.9879
1.500 0.3252 0.00550 0.00138 -0.0180 0.5137 0.9916
1.750 0.3622 0.00559 0.00141 -0.0200 0.4994 0.9947
2.000 0.4025 0.00564 0.00139 -0.0228 0.4848 0.9971
2.250 0.4420 0.00569 0.00138 -0.0254 0.4705 0.9997
2.500 0.4694 0.00575 0.00140 -0.0253 0.4572 1.0000
2.750 0.4950 0.00583 0.00143 -0.0249 0.4445 1.0000
3.000 0.5206 0.00591 0.00148 -0.0244 0.4305 1.0000
3.250 0.5462 0.00601 0.00152 -0.0240 0.4159 1.0000
3.500 0.5718 0.00611 0.00158 -0.0236 0.4009 1.0000
3.750 0.5974 0.00622 0.00165 -0.0231 0.3865 1.0000
4.000 0.6230 0.00635 0.00174 -0.0227 0.3704 1.0000
4.250 0.6485 0.00649 0.00183 -0.0223 0.3539 1.0000
4.500 0.6736 0.00668 0.00194 -0.0218 0.3319 1.0000
4.750 0.6984 0.00692 0.00207 -0.0213 0.3052 1.0000
5.000 0.7230 0.00718 0.00224 -0.0208 0.2771 1.0000
5.250 0.7474 0.00747 0.00242 -0.0203 0.2499 1.0000
5.500 0.7718 0.00774 0.00261 -0.0197 0.2260 1.0000
5.750 0.7959 0.00806 0.00284 -0.0191 0.2010 1.0000
6.000 0.8192 0.00846 0.00310 -0.0185 0.1703 1.0000
6.250 0.8424 0.00887 0.00338 -0.0178 0.1432 1.0000
6.500 0.8653 0.00928 0.00369 -0.0171 0.1189 1.0000
6.750 0.8880 0.00972 0.00402 -0.0163 0.0959 1.0000
7.000 0.9102 0.01019 0.00439 -0.0154 0.0750 1.0000
7.250 0.9319 0.01070 0.00479 -0.0146 0.0540 1.0000
7.500 0.9519 0.01140 0.00533 -0.0134 0.0289 1.0000
7.750 0.9720 0.01208 0.00593 -0.0122 0.0163 1.0000
8.000 0.9940 0.01249 0.00639 -0.0112 0.0148 1.0000
8.250 1.0151 0.01298 0.00691 -0.0102 0.0132 1.0000
8.500 1.0350 0.01360 0.00760 -0.0089 0.0121 1.0000
8.750 1.0552 0.01415 0.00822 -0.0077 0.0116 1.0000
9.000 1.0754 0.01466 0.00880 -0.0065 0.0112 1.0000
9.250 1.0947 0.01524 0.00946 -0.0052 0.0109 1.0000
9.500 1.1133 0.01587 0.01016 -0.0039 0.0105 1.0000
9.750 1.1314 0.01650 0.01086 -0.0025 0.0102 1.0000
10.000 1.1486 0.01718 0.01160 -0.0010 0.0097 1.0000
10.250 1.1644 0.01794 0.01243 0.0006 0.0092 1.0000
10.500 1.1769 0.01893 0.01350 0.0026 0.0089 1.0000
10.750 1.1825 0.02040 0.01509 0.0055 0.0085 1.0000
11.000 1.1832 0.02213 0.01696 0.0088 0.0083 1.0000
11.250 1.1954 0.02281 0.01772 0.0108 0.0082 1.0000
11.500 1.2026 0.02359 0.01858 0.0134 0.0080 1.0000
11.750 1.2070 0.02466 0.01975 0.0160 0.0079 1.0000
12.000 1.2121 0.02589 0.02107 0.0179 0.0077 1.0000
12.250 1.2170 0.02729 0.02256 0.0194 0.0076 1.0000
12.500 1.2201 0.02902 0.02439 0.0205 0.0074 1.0000
12.750 1.2252 0.03069 0.02615 0.0212 0.0072 1.0000
13.000 1.2280 0.03273 0.02830 0.0217 0.0070 1.0000
13.250 1.2321 0.03475 0.03040 0.0219 0.0068 1.0000
13.500 1.2332 0.03720 0.03295 0.0218 0.0067 1.0000
13.750 1.2327 0.03992 0.03578 0.0216 0.0066 1.0000
14.000 1.2342 0.04256 0.03848 0.0209 0.0063 1.0000
14.250 1.2319 0.04570 0.04172 0.0203 0.0063 1.0000
14.500 1.2276 0.04919 0.04534 0.0194 0.0063 1.0000
14.750 1.2220 0.05296 0.04920 0.0181 0.0062 1.0000
15.000 1.2124 0.05734 0.05370 0.0167 0.0061 1.0000
15.250 1.2038 0.06170 0.05816 0.0150 0.0060 1.0000
15.500 1.1867 0.06746 0.06405 0.0129 0.0058 1.0000
15.750 1.1838 0.07155 0.06825 0.0109 0.0060 1.0000
16.000 1.1577 0.07914 0.07601 0.0077 0.0058 1.0000
16.250 1.1514 0.08410 0.08106 0.0052 0.0058 1.0000
16.500 1.1310 0.09147 0.08859 0.0016 0.0057 1.0000
16.750 1.1121 0.09908 0.09634 -0.0023 0.0057 1.0000
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