NACA 64-110 AIRFOIL (n64110-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-110 AIRFOIL (n64110-il) Reynolds number: 50,000 Max Cl/Cd: 29.88 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64110-il-50000.txt Download as CSV file: xf-n64110-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-110 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5133 0.09743 0.09047 0.0141 1.0000 0.3997
-8.250 -0.5074 0.09400 0.08707 0.0142 1.0000 0.4136
-8.000 -0.5051 0.09078 0.08390 0.0142 1.0000 0.4259
-7.750 -0.5989 0.07730 0.07086 -0.0091 1.0000 0.2605
-7.500 -0.6583 0.06278 0.05594 -0.0263 1.0000 0.1756
-7.250 -0.6640 0.05605 0.04848 -0.0288 1.0000 0.1491
-7.000 -0.6559 0.05093 0.04285 -0.0288 1.0000 0.1384
-6.750 -0.6398 0.04692 0.03850 -0.0282 1.0000 0.1322
-6.500 -0.6255 0.04284 0.03371 -0.0274 1.0000 0.1248
-6.250 -0.6068 0.03980 0.03003 -0.0262 1.0000 0.1212
-6.000 -0.5858 0.03673 0.02660 -0.0251 1.0000 0.1202
-5.750 -0.5648 0.03446 0.02376 -0.0238 1.0000 0.1225
-5.500 -0.5422 0.03171 0.02108 -0.0230 1.0000 0.1277
-5.250 -0.5180 0.02959 0.01867 -0.0218 1.0000 0.1312
-5.000 -0.4927 0.02783 0.01658 -0.0204 1.0000 0.1363
-4.750 -0.4689 0.02608 0.01493 -0.0191 1.0000 0.1495
-4.500 -0.4456 0.02451 0.01345 -0.0174 1.0000 0.1639
-4.250 -0.4274 0.02293 0.01212 -0.0154 1.0000 0.1864
-4.000 -0.4139 0.02102 0.01064 -0.0132 1.0000 0.2368
-3.750 -0.4263 0.01859 0.01096 -0.0040 1.0000 0.6309
-3.500 -0.2221 0.02564 0.01662 -0.0061 1.0000 0.9323
-3.250 -0.1678 0.02454 0.01515 -0.0123 1.0000 0.9548
-3.000 -0.1194 0.02343 0.01374 -0.0178 1.0000 0.9715
-2.750 -0.0703 0.02227 0.01236 -0.0237 1.0000 0.9860
-2.500 -0.0218 0.02118 0.01108 -0.0296 1.0000 0.9997
-2.250 -0.0082 0.02076 0.01061 -0.0290 1.0000 1.0000
-2.000 0.0020 0.02043 0.01029 -0.0279 1.0000 1.0000
-1.750 0.0081 0.02021 0.01009 -0.0260 1.0000 1.0000
-1.500 0.0080 0.02010 0.01002 -0.0233 1.0000 1.0000
-1.250 0.0014 0.02010 0.01004 -0.0196 1.0000 1.0000
-1.000 -0.0103 0.02014 0.01009 -0.0152 1.0000 1.0000
-0.750 -0.0243 0.02013 0.01010 -0.0106 1.0000 1.0000
-0.500 -0.0392 0.02006 0.01003 -0.0059 1.0000 1.0000
-0.250 -0.0544 0.01991 0.00987 -0.0012 1.0000 1.0000
0.000 -0.0675 0.01971 0.00964 0.0032 1.0000 1.0000
0.250 -0.0738 0.01958 0.00944 0.0067 1.0000 1.0000
0.500 -0.0685 0.01962 0.00939 0.0085 1.0000 1.0000
0.750 -0.0559 0.01982 0.00949 0.0092 1.0000 1.0000
1.000 -0.0401 0.02012 0.00971 0.0095 1.0000 1.0000
1.250 -0.0228 0.02049 0.01001 0.0095 1.0000 1.0000
1.500 -0.0047 0.02092 0.01039 0.0095 1.0000 1.0000
1.750 0.0138 0.02140 0.01084 0.0094 1.0000 1.0000
2.000 0.0324 0.02193 0.01135 0.0092 1.0000 1.0000
2.250 0.0661 0.02284 0.01229 0.0062 0.9937 1.0000
2.500 0.1089 0.02400 0.01352 0.0015 0.9830 1.0000
2.750 0.1480 0.02505 0.01467 -0.0024 0.9715 1.0000
3.000 0.1856 0.02609 0.01583 -0.0059 0.9593 1.0000
3.250 0.2227 0.02715 0.01703 -0.0093 0.9466 1.0000
3.500 0.2604 0.02824 0.01832 -0.0126 0.9328 1.0000
3.750 0.2994 0.02934 0.01964 -0.0160 0.9174 1.0000
4.000 0.3465 0.03050 0.02109 -0.0203 0.8992 1.0000
4.250 0.3846 0.03134 0.02227 -0.0227 0.8757 1.0000
4.500 0.5760 0.02279 0.01521 -0.0264 0.7238 1.0000
4.750 0.5808 0.01944 0.01157 -0.0117 0.5116 1.0000
5.000 0.5724 0.02296 0.01239 -0.0053 0.2196 1.0000
5.250 0.5892 0.02517 0.01414 -0.0034 0.1764 1.0000
5.500 0.6160 0.02710 0.01590 -0.0025 0.1528 1.0000
5.750 0.6482 0.02925 0.01789 -0.0022 0.1370 1.0000
6.000 0.6798 0.03136 0.02026 -0.0017 0.1288 1.0000
6.250 0.7076 0.03387 0.02288 -0.0013 0.1210 1.0000
6.500 0.7334 0.03644 0.02589 -0.0005 0.1176 1.0000
6.750 0.7577 0.03949 0.02944 0.0004 0.1173 1.0000
7.000 0.7789 0.04288 0.03330 0.0014 0.1183 1.0000
7.250 0.7960 0.04639 0.03731 0.0025 0.1187 1.0000
7.500 0.8098 0.05011 0.04150 0.0035 0.1193 1.0000
7.750 0.8225 0.05430 0.04605 0.0043 0.1213 1.0000
8.000 0.8238 0.05909 0.05158 0.0052 0.1300 1.0000
8.250 0.8271 0.06441 0.05730 0.0054 0.1405 1.0000
8.500 0.8105 0.07085 0.06421 0.0042 0.1559 1.0000
8.750 0.7796 0.07803 0.07162 0.0010 0.1722 1.0000
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Polar data table (+)
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