NACA 6412 (naca6412-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 6412 (naca6412-il) Reynolds number: 50,000 Max Cl/Cd: 9.81 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca6412-il-50000.txt Download as CSV file: xf-naca6412-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6412
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3304 0.13030 0.12383 -0.0292 1.0001 0.1748
-8.750 -0.3583 0.13182 0.12550 -0.0274 1.0001 0.1754
-8.500 -0.3148 0.12222 0.11582 -0.0254 1.0001 0.1826
-8.250 -0.3221 0.12090 0.11458 -0.0236 1.0001 0.1873
-8.000 -0.3420 0.12106 0.11486 -0.0218 1.0001 0.1909
-7.750 -0.3716 0.12225 0.11619 -0.0194 1.0001 0.1923
-7.500 -0.4036 0.12347 0.11758 -0.0172 1.0001 0.1930
-7.250 -0.3607 0.11491 0.10895 -0.0157 1.0001 0.1997
-7.000 -0.3705 0.11359 0.10771 -0.0133 1.0001 0.2039
-6.750 -0.3921 0.11331 0.10754 -0.0107 1.0001 0.2075
-6.500 -0.4215 0.11416 0.10853 -0.0116 1.0001 0.2104
-6.250 -0.4238 0.11077 0.10522 -0.0102 1.0001 0.2128
-6.000 -0.4156 0.10733 0.10179 -0.0065 1.0001 0.2177
-5.750 -0.4218 0.10560 0.10013 -0.0058 1.0001 0.2238
-5.500 -0.4384 0.10518 0.09978 -0.0126 1.0001 0.2297
-5.250 -0.4318 0.10107 0.09572 -0.0059 1.0001 0.2341
-5.000 -0.4327 0.09919 0.09386 -0.0060 1.0001 0.2435
-4.750 -0.4335 0.09652 0.09123 -0.0079 1.0001 0.2501
-4.500 -0.4305 0.09419 0.08894 -0.0058 1.0001 0.2592
-4.250 -0.4270 0.09151 0.08628 -0.0084 1.0001 0.2687
-4.000 -0.4173 0.08945 0.08418 -0.0133 1.0001 0.2837
-3.750 -0.3873 0.08592 0.08059 -0.0182 0.9930 0.3015
-3.500 -0.3563 0.08220 0.07685 -0.0206 0.9829 0.3215
-3.250 -0.3242 0.07938 0.07395 -0.0259 0.9723 0.3544
-3.000 -0.3042 0.07643 0.07101 -0.0252 0.9622 0.3773
-2.750 -0.2800 0.07380 0.06835 -0.0265 0.9523 0.4126
-2.500 -0.2622 0.07155 0.06613 -0.0247 0.9436 0.4643
-2.250 -0.0529 0.05589 0.04808 -0.0876 0.9317 0.2070
-2.000 -0.0005 0.05297 0.04454 -0.0944 0.9228 0.2079
-1.750 0.0439 0.05090 0.04195 -0.0990 0.9135 0.2138
-1.500 0.0783 0.04999 0.04076 -0.1014 0.9041 0.2246
-1.250 0.1235 0.04895 0.03939 -0.1053 0.8955 0.2381
-1.000 0.1507 0.04848 0.03863 -0.1063 0.8858 0.2517
-0.750 0.1967 0.04802 0.03794 -0.1099 0.8781 0.2739
-0.500 0.2151 0.04806 0.03785 -0.1095 0.8685 0.2907
-0.250 0.2630 0.04779 0.03739 -0.1132 0.8611 0.3230
0.000 0.2776 0.04812 0.03764 -0.1121 0.8515 0.3451
0.250 0.3266 0.04795 0.03740 -0.1158 0.8445 0.3941
0.500 0.3387 0.04843 0.03797 -0.1145 0.8354 0.4291
0.750 0.3841 0.04803 0.03809 -0.1175 0.8286 0.5310
1.000 0.3871 0.04738 0.03867 -0.1139 0.8205 0.9999
1.250 0.4254 0.04852 0.03904 -0.1163 0.8130 0.9999
1.500 0.4386 0.04991 0.04017 -0.1154 0.8050 0.9999
1.750 0.4645 0.05112 0.04112 -0.1160 0.7976 0.9999
2.000 0.4843 0.05252 0.04233 -0.1159 0.7905 0.9999
2.250 0.4988 0.05398 0.04366 -0.1153 0.7833 0.9999
2.500 0.5342 0.05516 0.04465 -0.1170 0.7765 0.9999
2.750 0.5333 0.05703 0.04647 -0.1147 0.7697 0.9999
3.000 0.5632 0.05831 0.04763 -0.1158 0.7628 0.9999
3.250 0.5723 0.06014 0.04939 -0.1148 0.7564 0.9999
3.500 0.5833 0.06193 0.05113 -0.1140 0.7502 0.9999
3.750 0.6202 0.06320 0.05230 -0.1157 0.7431 0.9999
4.000 0.6139 0.06554 0.05465 -0.1134 0.7382 0.9999
4.250 0.6273 0.06743 0.05651 -0.1130 0.7325 0.9999
4.500 0.6555 0.06903 0.05806 -0.1139 0.7252 0.9999
4.750 0.6527 0.07151 0.06055 -0.1123 0.7217 0.9999
5.000 0.6602 0.07377 0.06282 -0.1116 0.7175 0.9999
5.250 0.6929 0.07535 0.06437 -0.1128 0.7086 0.9999
5.500 0.6905 0.07809 0.06714 -0.1115 0.7067 0.9999
5.750 0.6933 0.08088 0.06996 -0.1109 0.7062 0.9999
6.000 0.7021 0.08387 0.07298 -0.1112 0.7080 0.9999
6.250 0.7197 0.08705 0.07620 -0.1123 0.7101 0.9999
6.500 0.6387 0.09319 0.08249 -0.1086 0.7826 0.9999
6.750 0.6586 0.09609 0.08541 -0.1095 0.7752 0.9999
7.000 0.6765 0.09828 0.08764 -0.1099 0.7629 0.9999
7.250 0.6788 0.10023 0.08962 -0.1086 0.7534 0.9999
7.500 0.7178 0.10418 0.09361 -0.1117 0.7437 0.9999
7.750 0.7125 0.10520 0.09468 -0.1093 0.7310 0.9999
8.000 0.7210 0.10767 0.09719 -0.1089 0.7213 0.9999
8.250 0.7611 0.11176 0.10136 -0.1119 0.7102 0.9999
8.500 0.7524 0.11275 0.10240 -0.1094 0.6972 0.9999
8.750 0.7588 0.11523 0.10494 -0.1088 0.6864 0.9999
9.000 0.7932 0.11926 0.10905 -0.1111 0.6760 0.9999
9.250 0.7950 0.12088 0.11076 -0.1098 0.6619 0.9999
9.500 0.7958 0.12308 0.11302 -0.1088 0.6495 0.9999
9.750 0.8108 0.12628 0.11631 -0.1093 0.6392 0.9999
10.000 0.8434 0.13017 0.12030 -0.1109 0.6255 0.9999
10.250 0.8399 0.13173 0.12194 -0.1095 0.6113 0.9999
10.500 0.8408 0.13412 0.12442 -0.1088 0.5981 0.9999
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Polar data table (+)
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