NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-108 AIRFOIL (n64108-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.12 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64108-il-1000000.txt Download as CSV file: xf-n64108-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6147 0.08216 0.08058 -0.0092 1.0000 0.0090
-9.000 -0.6205 0.07484 0.07330 -0.0154 1.0000 0.0090
-8.750 -0.6317 0.06835 0.06678 -0.0216 1.0000 0.0090
-8.500 -0.6461 0.06398 0.06235 -0.0233 1.0000 0.0090
-8.250 -0.6518 0.05908 0.05733 -0.0246 1.0000 0.0090
-8.000 -0.6541 0.05404 0.05215 -0.0254 1.0000 0.0090
-7.750 -0.6527 0.04905 0.04698 -0.0256 1.0000 0.0090
-7.500 -0.6650 0.03944 0.03696 -0.0254 1.0000 0.0092
-7.000 -0.6553 0.02622 0.02284 -0.0233 1.0000 0.0075
-6.750 -0.6405 0.02033 0.01631 -0.0216 1.0000 0.0081
-6.500 -0.6177 0.01850 0.01423 -0.0209 1.0000 0.0086
-6.250 -0.5928 0.01782 0.01340 -0.0205 1.0000 0.0089
-6.000 -0.5729 0.01452 0.00969 -0.0194 1.0000 0.0093
-5.750 -0.5510 0.01285 0.00788 -0.0186 1.0000 0.0101
-5.500 -0.5267 0.01260 0.00763 -0.0181 1.0000 0.0110
-5.250 -0.4998 0.01210 0.00708 -0.0182 0.9984 0.0120
-5.000 -0.4664 0.01130 0.00620 -0.0196 0.9927 0.0128
-4.750 -0.4326 0.01067 0.00550 -0.0210 0.9866 0.0135
-4.500 -0.3983 0.01024 0.00502 -0.0226 0.9799 0.0140
-4.250 -0.3673 0.00888 0.00352 -0.0237 0.9699 0.0161
-4.000 -0.3376 0.00855 0.00316 -0.0242 0.9577 0.0179
-3.750 -0.3105 0.00826 0.00280 -0.0240 0.9443 0.0194
-3.500 -0.2845 0.00804 0.00251 -0.0235 0.9312 0.0208
-3.250 -0.2586 0.00772 0.00209 -0.0231 0.9186 0.0239
-3.000 -0.2323 0.00749 0.00184 -0.0227 0.9067 0.0311
-2.750 -0.2059 0.00726 0.00160 -0.0224 0.8950 0.0433
-2.500 -0.1800 0.00680 0.00136 -0.0222 0.8837 0.1172
-2.250 -0.1555 0.00589 0.00108 -0.0222 0.8725 0.3105
-2.000 -0.1306 0.00509 0.00091 -0.0221 0.8614 0.5037
-1.750 -0.1040 0.00482 0.00086 -0.0219 0.8506 0.5815
-1.500 -0.0768 0.00472 0.00081 -0.0218 0.8399 0.6163
-1.250 -0.0495 0.00465 0.00077 -0.0217 0.8292 0.6460
-1.000 -0.0224 0.00455 0.00077 -0.0215 0.8185 0.6859
-0.750 0.0046 0.00447 0.00078 -0.0213 0.8079 0.7259
-0.500 0.0321 0.00445 0.00078 -0.0211 0.7973 0.7489
-0.250 0.0597 0.00444 0.00078 -0.0210 0.7865 0.7636
0.000 0.0875 0.00445 0.00078 -0.0209 0.7756 0.7763
0.250 0.1152 0.00445 0.00079 -0.0209 0.7638 0.7874
0.500 0.1428 0.00446 0.00080 -0.0208 0.7507 0.7986
0.750 0.1702 0.00450 0.00081 -0.0206 0.7339 0.8098
1.000 0.1974 0.00455 0.00082 -0.0204 0.7087 0.8210
1.250 0.2242 0.00465 0.00083 -0.0202 0.6730 0.8323
1.500 0.2509 0.00476 0.00087 -0.0199 0.6390 0.8437
1.750 0.2778 0.00484 0.00092 -0.0197 0.6115 0.8553
2.000 0.3045 0.00496 0.00099 -0.0194 0.5786 0.8668
2.250 0.3301 0.00523 0.00107 -0.0190 0.5136 0.8786
2.500 0.3541 0.00579 0.00123 -0.0185 0.3884 0.8909
2.750 0.3756 0.00685 0.00158 -0.0179 0.1934 0.9044
3.000 0.3982 0.00763 0.00190 -0.0172 0.0641 0.9186
3.250 0.4225 0.00795 0.00213 -0.0165 0.0353 0.9333
3.500 0.4471 0.00811 0.00233 -0.0157 0.0290 0.9497
3.750 0.4738 0.00844 0.00272 -0.0154 0.0223 0.9687
4.000 0.5078 0.00869 0.00301 -0.0169 0.0196 0.9871
4.250 0.5379 0.00905 0.00338 -0.0176 0.0173 1.0000
4.500 0.5623 0.00997 0.00441 -0.0171 0.0149 1.0000
4.750 0.5888 0.01038 0.00485 -0.0170 0.0145 1.0000
5.000 0.6148 0.01089 0.00543 -0.0167 0.0140 1.0000
5.250 0.6404 0.01148 0.00608 -0.0165 0.0134 1.0000
5.500 0.6660 0.01209 0.00674 -0.0162 0.0126 1.0000
5.750 0.6922 0.01250 0.00717 -0.0160 0.0116 1.0000
6.000 0.7178 0.01299 0.00766 -0.0159 0.0106 1.0000
6.250 0.7375 0.01575 0.01067 -0.0146 0.0097 1.0000
6.500 0.7621 0.01693 0.01200 -0.0142 0.0094 1.0000
6.750 0.7874 0.01766 0.01284 -0.0139 0.0090 1.0000
7.000 0.8115 0.01895 0.01431 -0.0133 0.0086 1.0000
7.250 0.8343 0.02067 0.01626 -0.0126 0.0079 1.0000
7.500 0.8546 0.02314 0.01902 -0.0117 0.0075 1.0000
7.750 0.8786 0.02345 0.01938 -0.0115 0.0070 1.0000
8.000 0.9022 0.02373 0.01973 -0.0114 0.0067 1.0000
8.250 0.9215 0.02535 0.02153 -0.0107 0.0064 1.0000
8.500 0.9275 0.03064 0.02737 -0.0087 0.0062 1.0000
10.500 0.6510 0.10102 0.09965 -0.0257 0.0096 1.0000
10.750 0.6461 0.10754 0.10616 -0.0286 0.0096 1.0000
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Polar data table (+)
Polar graphs
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