NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-108 AIRFOIL (n64108-il) Reynolds number: 100,000 Max Cl/Cd: 36.22 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64108-il-100000-n5.txt Download as CSV file: xf-n64108-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-108 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5126 0.09431 0.08967 -0.0045 1.0000 0.0296
-9.500 -0.5178 0.08860 0.08400 -0.0070 1.0000 0.0283
-9.000 -0.6164 0.08640 0.08159 -0.0097 1.0000 0.0273
-8.500 -0.6365 0.07247 0.06753 -0.0224 1.0000 0.0237
-8.250 -0.6412 0.06786 0.06285 -0.0237 1.0000 0.0233
-8.000 -0.6441 0.06315 0.05801 -0.0250 1.0000 0.0231
-7.750 -0.6439 0.05849 0.05316 -0.0258 1.0000 0.0229
-7.500 -0.6400 0.05403 0.04846 -0.0262 1.0000 0.0227
-7.250 -0.6331 0.04961 0.04374 -0.0263 1.0000 0.0226
-7.000 -0.6232 0.04530 0.03906 -0.0261 1.0000 0.0226
-6.750 -0.6103 0.04126 0.03459 -0.0256 1.0000 0.0228
-6.500 -0.5921 0.03874 0.03146 -0.0247 1.0000 0.0241
-6.250 -0.5788 0.03430 0.02673 -0.0245 1.0000 0.0258
-6.000 -0.5593 0.03167 0.02376 -0.0239 1.0000 0.0270
-5.750 -0.5379 0.02901 0.02070 -0.0231 1.0000 0.0277
-5.500 -0.5152 0.02670 0.01803 -0.0223 1.0000 0.0287
-5.250 -0.4918 0.02473 0.01574 -0.0214 1.0000 0.0301
-5.000 -0.4679 0.02338 0.01406 -0.0206 1.0000 0.0338
-4.750 -0.4439 0.02190 0.01234 -0.0197 1.0000 0.0354
-4.500 -0.4208 0.02044 0.01075 -0.0186 1.0000 0.0365
-4.250 -0.4002 0.01885 0.00919 -0.0175 1.0000 0.0386
-4.000 -0.3795 0.01782 0.00815 -0.0164 1.0000 0.0415
-3.750 -0.3586 0.01706 0.00732 -0.0153 1.0000 0.0470
-3.500 -0.3383 0.01625 0.00645 -0.0142 1.0000 0.0546
-3.250 -0.3173 0.01561 0.00570 -0.0131 1.0000 0.0628
-3.000 -0.2969 0.01483 0.00504 -0.0121 1.0000 0.0864
-2.750 -0.2806 0.01278 0.00434 -0.0114 1.0000 0.3469
-2.500 -0.2660 0.01186 0.00442 -0.0089 1.0000 0.5944
-2.250 -0.2422 0.01172 0.00479 -0.0070 0.9908 0.7349
-2.000 -0.2198 0.01194 0.00518 -0.0040 0.9802 0.8205
-1.750 -0.1863 0.01197 0.00508 -0.0049 0.9714 0.8436
-1.500 -0.1486 0.01195 0.00491 -0.0070 0.9639 0.8568
-1.250 -0.1135 0.01192 0.00477 -0.0084 0.9546 0.8698
-1.000 -0.0786 0.01189 0.00463 -0.0099 0.9455 0.8826
-0.750 -0.0410 0.01187 0.00453 -0.0118 0.9379 0.8947
-0.500 -0.0066 0.01184 0.00446 -0.0131 0.9277 0.9073
-0.250 0.0295 0.01181 0.00439 -0.0148 0.9184 0.9198
0.000 0.0679 0.01178 0.00433 -0.0169 0.9101 0.9314
0.250 0.1049 0.01176 0.00431 -0.0189 0.8999 0.9436
0.500 0.1431 0.01173 0.00430 -0.0211 0.8900 0.9553
0.750 0.1827 0.01171 0.00430 -0.0236 0.8808 0.9664
1.000 0.2224 0.01169 0.00432 -0.0261 0.8707 0.9775
1.250 0.2620 0.01167 0.00440 -0.0288 0.8598 0.9888
1.500 0.2977 0.01168 0.00449 -0.0306 0.8486 1.0000
1.750 0.3199 0.01176 0.00463 -0.0297 0.8360 1.0000
2.000 0.3425 0.01186 0.00479 -0.0288 0.8237 1.0000
2.250 0.3652 0.01196 0.00500 -0.0277 0.8097 1.0000
2.500 0.3878 0.01205 0.00518 -0.0265 0.7927 1.0000
2.750 0.4052 0.01189 0.00490 -0.0230 0.7437 1.0000
3.000 0.4205 0.01187 0.00452 -0.0190 0.6468 1.0000
3.250 0.4408 0.01217 0.00453 -0.0170 0.5546 1.0000
3.500 0.4546 0.01352 0.00474 -0.0145 0.2968 1.0000
3.750 0.4695 0.01570 0.00568 -0.0134 0.0833 1.0000
4.000 0.4922 0.01665 0.00655 -0.0126 0.0627 1.0000
4.250 0.5151 0.01751 0.00741 -0.0120 0.0502 1.0000
4.500 0.5382 0.01838 0.00842 -0.0112 0.0445 1.0000
4.750 0.5602 0.01950 0.00957 -0.0104 0.0408 1.0000
5.000 0.5821 0.02107 0.01118 -0.0095 0.0385 1.0000
5.250 0.6068 0.02236 0.01263 -0.0088 0.0365 1.0000
5.500 0.6318 0.02356 0.01400 -0.0083 0.0324 1.0000
5.750 0.6567 0.02520 0.01581 -0.0077 0.0304 1.0000
6.000 0.6812 0.02718 0.01799 -0.0072 0.0290 1.0000
6.250 0.7047 0.02960 0.02067 -0.0066 0.0280 1.0000
6.500 0.7261 0.03281 0.02424 -0.0059 0.0272 1.0000
6.750 0.7460 0.03549 0.02751 -0.0049 0.0255 1.0000
7.000 0.7649 0.03830 0.03089 -0.0037 0.0238 1.0000
7.250 0.7798 0.04205 0.03516 -0.0026 0.0234 1.0000
7.500 0.7915 0.04616 0.03975 -0.0015 0.0231 1.0000
7.750 0.7997 0.05049 0.04451 -0.0005 0.0231 1.0000
8.000 0.8042 0.05504 0.04942 0.0002 0.0232 1.0000
8.250 0.8051 0.05965 0.05434 0.0007 0.0234 1.0000
8.500 0.8017 0.06430 0.05924 0.0008 0.0235 1.0000
8.750 0.7938 0.06898 0.06411 0.0005 0.0236 1.0000
9.000 0.7816 0.07327 0.06852 0.0000 0.0239 1.0000
9.250 0.7668 0.07810 0.07343 -0.0020 0.0241 1.0000
9.500 0.7544 0.08376 0.07913 -0.0059 0.0244 1.0000
9.750 0.7447 0.09061 0.08599 -0.0112 0.0247 1.0000
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Polar data table (+)
Polar graphs
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