NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-1T AIRFOIL (nlr1t-il) Reynolds number: 50,000 Max Cl/Cd: 29.6 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlr1t-il-50000.txt Download as CSV file: xf-nlr1t-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-1T AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5108 0.10563 0.09885 -0.0017 1.0000 0.2815
-8.500 -0.5138 0.10288 0.09618 -0.0015 1.0000 0.2979
-8.250 -0.5226 0.10051 0.09390 -0.0014 1.0000 0.3139
-8.000 -0.4949 0.09575 0.08909 0.0012 1.0000 0.3370
-7.750 -0.5113 0.09410 0.08757 0.0019 1.0000 0.3578
-7.500 -0.4946 0.09043 0.08391 0.0044 1.0000 0.3861
-7.250 -0.4883 0.08757 0.08110 0.0069 1.0000 0.4159
-7.000 -0.4677 0.08380 0.07733 0.0097 1.0000 0.4501
-6.750 -0.4622 0.08150 0.07509 0.0131 1.0000 0.4893
-6.500 -0.4482 0.07875 0.07237 0.0167 1.0000 0.5339
-6.250 -0.4071 0.07433 0.06787 0.0185 1.0000 0.5872
-5.000 -0.5425 0.04968 0.04221 -0.0092 1.0000 0.2079
-4.750 -0.5202 0.04482 0.03616 -0.0089 1.0000 0.1522
-4.500 -0.5003 0.04131 0.03217 -0.0073 1.0000 0.1360
-4.250 -0.4798 0.03892 0.02888 -0.0050 1.0000 0.1244
-4.000 -0.4589 0.03616 0.02589 -0.0036 1.0000 0.1229
-3.750 -0.4365 0.03384 0.02322 -0.0022 1.0000 0.1217
-3.500 -0.4119 0.03167 0.02072 -0.0010 1.0000 0.1198
-3.250 -0.3857 0.02974 0.01842 0.0002 1.0000 0.1183
-3.000 -0.3583 0.02805 0.01644 0.0011 1.0000 0.1187
-2.750 -0.3294 0.02659 0.01474 0.0019 1.0000 0.1218
-2.500 -0.2991 0.02516 0.01330 0.0021 1.0000 0.1314
-2.250 -0.1320 0.01903 0.01034 -0.0191 1.0000 1.0000
-2.000 -0.1191 0.01896 0.00982 -0.0164 1.0000 1.0000
-1.750 -0.1056 0.01892 0.00942 -0.0140 1.0000 1.0000
-1.500 -0.0914 0.01891 0.00912 -0.0117 1.0000 1.0000
-1.250 -0.0764 0.01893 0.00888 -0.0096 1.0000 1.0000
-1.000 -0.0608 0.01896 0.00869 -0.0076 1.0000 1.0000
-0.750 -0.0447 0.01902 0.00855 -0.0057 1.0000 1.0000
-0.500 -0.0283 0.01910 0.00844 -0.0038 1.0000 1.0000
-0.250 -0.0116 0.01921 0.00840 -0.0021 1.0000 1.0000
0.000 0.0055 0.01933 0.00839 -0.0004 1.0000 1.0000
0.250 0.0230 0.01948 0.00843 0.0012 1.0000 1.0000
0.500 0.0407 0.01965 0.00850 0.0027 1.0000 1.0000
0.750 0.0586 0.01985 0.00863 0.0041 1.0000 1.0000
1.000 0.0767 0.02008 0.00880 0.0054 1.0000 1.0000
1.250 0.0949 0.02033 0.00903 0.0066 1.0000 1.0000
1.500 0.1131 0.02062 0.00930 0.0078 1.0000 1.0000
1.750 0.1313 0.02095 0.00963 0.0089 1.0000 1.0000
2.000 0.1493 0.02133 0.01003 0.0099 1.0000 1.0000
2.250 0.1670 0.02176 0.01050 0.0109 1.0000 1.0000
2.500 0.1843 0.02226 0.01107 0.0117 1.0000 1.0000
2.750 0.2009 0.02284 0.01174 0.0125 1.0000 1.0000
3.000 0.2165 0.02355 0.01254 0.0132 1.0000 1.0000
3.250 0.3358 0.02479 0.01423 -0.0054 0.9547 1.0000
3.500 0.4659 0.02393 0.01410 -0.0225 0.8879 1.0000
3.750 0.5419 0.02095 0.01170 -0.0249 0.7580 1.0000
4.000 0.6014 0.02032 0.00960 -0.0239 0.5321 1.0000
4.250 0.6265 0.02166 0.01044 -0.0228 0.4719 1.0000
4.500 0.6544 0.02281 0.01137 -0.0225 0.4366 1.0000
4.750 0.6812 0.02390 0.01239 -0.0221 0.4096 1.0000
5.000 0.7077 0.02503 0.01353 -0.0216 0.3882 1.0000
5.250 0.7322 0.02619 0.01476 -0.0209 0.3680 1.0000
5.500 0.7564 0.02743 0.01601 -0.0201 0.3492 1.0000
5.750 0.7779 0.02868 0.01735 -0.0189 0.3278 1.0000
6.000 0.7988 0.02987 0.01846 -0.0176 0.3041 1.0000
6.250 0.8176 0.03124 0.02004 -0.0160 0.2802 1.0000
6.500 0.8371 0.03280 0.02160 -0.0145 0.2569 1.0000
6.750 0.8553 0.03469 0.02367 -0.0128 0.2349 1.0000
7.000 0.8747 0.03687 0.02590 -0.0113 0.2171 1.0000
7.250 0.8922 0.03904 0.02815 -0.0097 0.2012 1.0000
7.500 0.9059 0.04147 0.03105 -0.0077 0.1892 1.0000
7.750 0.9163 0.04483 0.03491 -0.0055 0.1827 1.0000
8.000 0.9248 0.04828 0.03882 -0.0033 0.1779 1.0000
8.250 0.9416 0.05117 0.04174 -0.0020 0.1721 1.0000
8.500 0.9363 0.05544 0.04664 0.0009 0.1695 1.0000
8.750 0.9303 0.05982 0.05145 0.0033 0.1671 1.0000
9.000 0.9213 0.06452 0.05648 0.0053 0.1662 1.0000
9.250 0.9067 0.06987 0.06208 0.0068 0.1675 1.0000
9.500 0.8915 0.07535 0.06772 0.0078 0.1697 1.0000
9.750 0.8858 0.08062 0.07306 0.0082 0.1718 1.0000
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