lrn1007 (lrn1007-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: lrn1007 (lrn1007-il) Reynolds number: 200,000 Max Cl/Cd: 81.74 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lrn1007-il-200000.txt Download as CSV file: xf-lrn1007-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: lrn1007
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1928 0.08883 0.08529 -0.0680 0.9456 0.0044
-7.750 -0.1814 0.08602 0.08248 -0.0706 0.9432 0.0062
-7.500 -0.1716 0.08358 0.08005 -0.0728 0.9404 0.0069
-7.250 -0.1613 0.08218 0.07866 -0.0753 0.9372 0.0082
-7.000 -0.1483 0.08054 0.07703 -0.0792 0.9343 0.0085
-6.750 -0.1322 0.07868 0.07515 -0.0838 0.9315 0.0087
-6.250 -0.0954 0.07409 0.07051 -0.0930 0.9277 0.0089
-6.000 -0.0754 0.07171 0.06809 -0.0970 0.9258 0.0090
-5.750 -0.0557 0.06920 0.06552 -0.1001 0.9237 0.0091
-5.500 -0.0356 0.06658 0.06284 -0.1027 0.9215 0.0091
-5.250 -0.0148 0.06394 0.06013 -0.1051 0.9193 0.0092
-5.000 0.0061 0.06115 0.05725 -0.1071 0.9176 0.0092
-4.750 0.0279 0.05847 0.05448 -0.1090 0.9163 0.0092
-4.500 0.0432 0.05451 0.05051 -0.1105 0.9142 0.0095
-4.250 0.0538 0.05008 0.04609 -0.1113 0.9122 0.0100
-4.000 0.0774 0.04828 0.04416 -0.1125 0.9104 0.0098
-3.750 0.0903 0.04456 0.04038 -0.1131 0.9087 0.0106
-3.500 0.1114 0.04189 0.03760 -0.1141 0.9068 0.0115
-3.250 0.1364 0.03949 0.03506 -0.1152 0.9052 0.0126
-3.000 0.1637 0.03720 0.03244 -0.1162 0.9039 0.0157
-2.750 0.1826 0.03584 0.03094 -0.1154 0.9015 0.0171
-2.500 0.2022 0.03499 0.02992 -0.1139 0.8984 0.0187
-2.250 0.2299 0.03548 0.03011 -0.1125 0.8962 0.0200
-2.000 0.2563 0.03479 0.02914 -0.1119 0.8942 0.0203
-1.750 0.2779 0.02985 0.02414 -0.1132 0.8924 0.0225
-1.500 0.3068 0.02790 0.02199 -0.1138 0.8910 0.0271
-1.250 0.3205 0.02854 0.02240 -0.1104 0.8868 0.0321
-1.000 0.3421 0.02622 0.01990 -0.1098 0.8831 0.0363
-0.750 0.3730 0.02484 0.01826 -0.1102 0.8807 0.0490
-0.500 0.4045 0.02340 0.01657 -0.1108 0.8789 0.0747
0.000 0.4418 0.02081 0.01387 -0.1089 0.8707 0.1890
0.250 0.4758 0.02056 0.01343 -0.1082 0.8681 0.1305
0.500 0.5121 0.02072 0.01328 -0.1076 0.8661 0.0580
0.750 0.5325 0.02027 0.01283 -0.1061 0.8614 0.0421
1.000 0.5566 0.02017 0.01263 -0.1052 0.8562 0.0326
1.250 0.5891 0.01931 0.01179 -0.1059 0.8533 0.0286
1.500 0.6084 0.01931 0.01171 -0.1045 0.8466 0.0266
1.750 0.6376 0.01911 0.01136 -0.1047 0.8420 0.0253
2.000 0.6718 0.01884 0.01104 -0.1054 0.8392 0.0272
2.250 0.6883 0.01812 0.01139 -0.1039 0.8308 0.5881
2.500 0.7379 0.01700 0.01092 -0.1078 0.8278 1.0000
2.750 0.7607 0.01716 0.01102 -0.1068 0.8207 1.0000
3.000 0.7898 0.01695 0.01077 -0.1065 0.8153 1.0000
3.250 0.8216 0.01241 0.00589 -0.0990 0.7662 1.0000
3.500 0.8425 0.01042 0.00381 -0.0951 0.6772 1.0000
3.750 0.8566 0.01048 0.00276 -0.0907 0.4907 1.0000
4.000 0.8519 0.01346 0.00406 -0.0862 0.1915 1.0000
4.250 0.8601 0.01553 0.00519 -0.0834 0.0138 1.0000
4.500 0.8832 0.01608 0.00600 -0.0822 0.0133 1.0000
4.750 0.9051 0.01681 0.00701 -0.0807 0.0146 1.0000
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Polar data table (+)
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