E220 (11.48%) (e220-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 500,000 Max Cl/Cd: 94.17 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e220-il-500000-n5.txt Download as CSV file: xf-e220-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E220 (11.48%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5176 0.08278 0.08003 -0.0215 0.7674 0.0053
-9.750 -0.5364 0.07501 0.07228 -0.0260 0.7608 0.0051
-9.250 -0.6857 0.04162 0.03831 -0.0364 0.7481 0.0047
-8.750 -0.7062 0.03107 0.02674 -0.0307 0.7375 0.0049
-8.500 -0.7002 0.02772 0.02292 -0.0284 0.7323 0.0050
-8.250 -0.6872 0.02541 0.02023 -0.0267 0.7276 0.0051
-8.000 -0.6709 0.02348 0.01796 -0.0252 0.7227 0.0053
-7.750 -0.6520 0.02196 0.01615 -0.0240 0.7180 0.0054
-7.500 -0.6311 0.02078 0.01473 -0.0230 0.7139 0.0057
-7.250 -0.6091 0.01971 0.01345 -0.0222 0.7100 0.0059
-7.000 -0.5857 0.01890 0.01245 -0.0215 0.7058 0.0061
-6.750 -0.5631 0.01788 0.01124 -0.0206 0.7017 0.0063
-6.500 -0.5421 0.01654 0.00969 -0.0195 0.6982 0.0065
-6.250 -0.5193 0.01560 0.00861 -0.0187 0.6945 0.0068
-6.000 -0.4951 0.01496 0.00788 -0.0181 0.6909 0.0072
-5.750 -0.4706 0.01438 0.00721 -0.0175 0.6875 0.0075
-5.500 -0.4458 0.01389 0.00661 -0.0169 0.6843 0.0080
-5.250 -0.4205 0.01340 0.00605 -0.0164 0.6808 0.0084
-5.000 -0.3951 0.01296 0.00552 -0.0160 0.6774 0.0090
-4.750 -0.3694 0.01255 0.00503 -0.0155 0.6743 0.0097
-4.500 -0.3438 0.01217 0.00460 -0.0151 0.6713 0.0112
-4.250 -0.3175 0.01188 0.00425 -0.0148 0.6684 0.0133
-4.000 -0.2914 0.01152 0.00387 -0.0144 0.6652 0.0161
-3.750 -0.2649 0.01125 0.00355 -0.0142 0.6621 0.0201
-3.500 -0.2385 0.01098 0.00327 -0.0139 0.6592 0.0267
-3.250 -0.2123 0.01071 0.00303 -0.0136 0.6564 0.0390
-3.000 -0.1862 0.01041 0.00282 -0.0133 0.6536 0.0629
-2.750 -0.1602 0.01008 0.00262 -0.0130 0.6506 0.0975
-2.500 -0.1340 0.00982 0.00245 -0.0128 0.6476 0.1301
-2.250 -0.1078 0.00956 0.00230 -0.0126 0.6447 0.1696
-2.000 -0.0822 0.00926 0.00216 -0.0123 0.6420 0.2242
-1.750 -0.0573 0.00888 0.00204 -0.0119 0.6394 0.3010
-1.500 -0.0321 0.00854 0.00195 -0.0115 0.6363 0.3731
-1.250 -0.0072 0.00823 0.00186 -0.0110 0.6332 0.4438
-1.000 0.0170 0.00791 0.00178 -0.0103 0.6303 0.5217
-0.750 0.0386 0.00749 0.00171 -0.0091 0.6277 0.6256
-0.500 0.0590 0.00706 0.00167 -0.0074 0.6248 0.7346
-0.250 0.0856 0.00671 0.00171 -0.0068 0.6215 0.8363
0.000 0.1519 0.00675 0.00188 -0.0149 0.6178 0.9056
0.250 0.1966 0.00690 0.00198 -0.0183 0.6142 0.9274
0.750 0.2573 0.00711 0.00213 -0.0192 0.6056 0.9530
1.000 0.2890 0.00720 0.00218 -0.0199 0.6013 0.9602
1.250 0.3232 0.00731 0.00223 -0.0213 0.5974 0.9667
1.500 0.3565 0.00738 0.00231 -0.0224 0.5922 0.9723
1.750 0.3952 0.00744 0.00233 -0.0248 0.5865 0.9761
2.000 0.4302 0.00751 0.00238 -0.0263 0.5811 0.9809
2.250 0.4652 0.00756 0.00243 -0.0279 0.5750 0.9846
2.500 0.5036 0.00758 0.00243 -0.0303 0.5689 0.9873
2.750 0.5401 0.00760 0.00246 -0.0323 0.5610 0.9904
3.000 0.5739 0.00764 0.00248 -0.0337 0.5532 0.9932
3.250 0.6078 0.00766 0.00250 -0.0351 0.5438 0.9952
3.500 0.6420 0.00766 0.00252 -0.0367 0.5335 0.9971
3.750 0.6753 0.00770 0.00253 -0.0380 0.5206 0.9989
4.000 0.7058 0.00777 0.00258 -0.0388 0.5049 1.0000
4.250 0.7308 0.00789 0.00266 -0.0384 0.4867 1.0000
4.500 0.7554 0.00805 0.00276 -0.0379 0.4638 1.0000
4.750 0.7797 0.00828 0.00290 -0.0374 0.4363 1.0000
5.000 0.8031 0.00861 0.00310 -0.0369 0.4022 1.0000
5.250 0.8258 0.00902 0.00337 -0.0363 0.3636 1.0000
5.500 0.8477 0.00952 0.00369 -0.0355 0.3227 1.0000
5.750 0.8694 0.01000 0.00402 -0.0348 0.2869 1.0000
6.000 0.8916 0.01040 0.00434 -0.0341 0.2611 1.0000
6.250 0.9124 0.01091 0.00471 -0.0332 0.2301 1.0000
6.500 0.9323 0.01146 0.00514 -0.0322 0.1961 1.0000
6.750 0.9517 0.01203 0.00557 -0.0311 0.1662 1.0000
7.000 0.9698 0.01266 0.00604 -0.0298 0.1356 1.0000
7.250 0.9874 0.01328 0.00653 -0.0284 0.1095 1.0000
7.500 1.0056 0.01381 0.00699 -0.0271 0.0932 1.0000
7.750 1.0234 0.01432 0.00746 -0.0256 0.0792 1.0000
8.000 1.0404 0.01485 0.00797 -0.0241 0.0672 1.0000
8.250 1.0565 0.01540 0.00849 -0.0224 0.0564 1.0000
8.500 1.0720 0.01594 0.00902 -0.0206 0.0476 1.0000
8.750 1.0860 0.01652 0.00959 -0.0186 0.0392 1.0000
9.000 1.0985 0.01713 0.01019 -0.0164 0.0319 1.0000
9.250 1.1089 0.01781 0.01085 -0.0139 0.0257 1.0000
9.500 1.1186 0.01844 0.01151 -0.0112 0.0221 1.0000
9.750 1.1204 0.01911 0.01221 -0.0072 0.0193 1.0000
10.000 1.1247 0.01977 0.01292 -0.0039 0.0178 1.0000
10.250 1.1300 0.02058 0.01378 -0.0012 0.0163 1.0000
10.500 1.1357 0.02155 0.01477 0.0012 0.0146 1.0000
10.750 1.1430 0.02255 0.01583 0.0032 0.0135 1.0000
11.000 1.1515 0.02355 0.01692 0.0049 0.0128 1.0000
11.250 1.1603 0.02462 0.01805 0.0064 0.0121 1.0000
11.500 1.1688 0.02575 0.01924 0.0078 0.0113 1.0000
11.750 1.1758 0.02705 0.02060 0.0092 0.0106 1.0000
12.000 1.1816 0.02850 0.02212 0.0105 0.0095 1.0000
12.250 1.1899 0.02979 0.02349 0.0116 0.0091 1.0000
12.500 1.1978 0.03114 0.02493 0.0126 0.0085 1.0000
12.750 1.2045 0.03264 0.02651 0.0136 0.0081 1.0000
13.000 1.2105 0.03423 0.02817 0.0145 0.0075 1.0000
13.250 1.2147 0.03601 0.03002 0.0153 0.0071 1.0000
13.500 1.2157 0.03814 0.03223 0.0162 0.0066 1.0000
13.750 1.2191 0.04009 0.03428 0.0169 0.0064 1.0000
14.000 1.2228 0.04205 0.03635 0.0175 0.0061 1.0000
14.250 1.2268 0.04403 0.03843 0.0179 0.0056 1.0000
14.500 1.2290 0.04625 0.04074 0.0183 0.0052 1.0000
14.750 1.2296 0.04875 0.04335 0.0185 0.0051 1.0000
15.000 1.2301 0.05135 0.04605 0.0186 0.0049 1.0000
15.250 1.2291 0.05421 0.04901 0.0185 0.0048 1.0000
15.500 1.2266 0.05735 0.05222 0.0182 0.0043 1.0000
15.750 1.2216 0.06093 0.05592 0.0176 0.0043 1.0000
16.000 1.2205 0.06412 0.05923 0.0171 0.0041 1.0000
16.250 1.2192 0.06739 0.06261 0.0164 0.0039 1.0000
16.500 1.2144 0.07128 0.06662 0.0154 0.0037 1.0000
16.750 1.2085 0.07546 0.07093 0.0142 0.0036 1.0000
17.000 1.2013 0.07995 0.07553 0.0127 0.0035 1.0000
17.250 1.1961 0.08424 0.07994 0.0112 0.0033 1.0000
17.500 1.1850 0.08961 0.08545 0.0092 0.0034 1.0000
17.750 1.1732 0.09528 0.09124 0.0069 0.0033 1.0000
18.000 1.1632 0.10075 0.09684 0.0046 0.0033 1.0000
18.250 1.1532 0.10637 0.10256 0.0021 0.0031 1.0000
18.500 1.1348 0.11366 0.11001 -0.0012 0.0033 1.0000
18.750 1.1257 0.11937 0.11582 -0.0039 0.0033 1.0000
19.000 1.1114 0.12619 0.12277 -0.0072 0.0032 1.0000
19.250 1.0956 0.13356 0.13025 -0.0109 0.0031 1.0000
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Polar data table (+)
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