NACA 64-008A AIRFOIL (n64008a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-008A AIRFOIL (n64008a-il) Reynolds number: 100,000 Max Cl/Cd: 30.11 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64008a-il-100000-n5.txt Download as CSV file: xf-n64008a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-008A 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6864 0.08802 0.08323 -0.0019 1.0000 0.0258
-9.000 -0.6932 0.08152 0.07674 -0.0075 1.0000 0.0253
-8.750 -0.7030 0.07603 0.07121 -0.0113 1.0000 0.0250
-8.500 -0.7118 0.07109 0.06617 -0.0132 1.0000 0.0247
-8.250 -0.7166 0.06610 0.06103 -0.0146 1.0000 0.0244
-8.000 -0.7183 0.06118 0.05590 -0.0152 1.0000 0.0240
-7.750 -0.7166 0.05632 0.05077 -0.0153 1.0000 0.0236
-7.500 -0.7117 0.05158 0.04570 -0.0150 1.0000 0.0233
-7.250 -0.7035 0.04707 0.04080 -0.0142 1.0000 0.0231
-7.000 -0.6924 0.04284 0.03614 -0.0132 1.0000 0.0231
-6.750 -0.6784 0.03895 0.03176 -0.0119 1.0000 0.0233
-6.500 -0.6619 0.03545 0.02776 -0.0106 1.0000 0.0238
-6.250 -0.6424 0.03282 0.02460 -0.0094 1.0000 0.0261
-6.000 -0.6209 0.03057 0.02181 -0.0081 1.0000 0.0275
-5.750 -0.5984 0.02823 0.01903 -0.0070 1.0000 0.0280
-5.500 -0.5757 0.02542 0.01594 -0.0061 1.0000 0.0289
-5.250 -0.5524 0.02335 0.01373 -0.0054 1.0000 0.0304
-5.000 -0.5292 0.02205 0.01229 -0.0047 1.0000 0.0334
-4.750 -0.5055 0.02092 0.01102 -0.0038 1.0000 0.0372
-4.500 -0.4827 0.01966 0.00966 -0.0028 1.0000 0.0389
-4.250 -0.4614 0.01848 0.00841 -0.0015 1.0000 0.0409
-4.000 -0.4409 0.01743 0.00733 -0.0003 1.0000 0.0448
-3.750 -0.4190 0.01666 0.00644 0.0008 1.0000 0.0511
-3.500 -0.3976 0.01584 0.00562 0.0018 1.0000 0.0682
-3.250 -0.3781 0.01461 0.00482 0.0029 1.0000 0.1385
-3.000 -0.3685 0.01223 0.00439 0.0054 1.0000 0.5296
-2.750 -0.3505 0.01177 0.00442 0.0081 1.0000 0.6661
-2.500 -0.3348 0.01165 0.00467 0.0120 1.0000 0.7751
-2.250 -0.3176 0.01173 0.00488 0.0158 1.0000 0.8422
-2.000 -0.2934 0.01173 0.00477 0.0172 1.0000 0.8706
-1.750 -0.2660 0.01168 0.00461 0.0173 1.0000 0.8875
-1.500 -0.2370 0.01164 0.00447 0.0170 1.0000 0.9036
-1.250 -0.2061 0.01161 0.00435 0.0162 1.0000 0.9196
-1.000 -0.1731 0.01161 0.00424 0.0148 1.0000 0.9356
-0.750 -0.1379 0.01161 0.00418 0.0128 1.0000 0.9513
-0.500 -0.0955 0.01164 0.00414 0.0093 0.9962 0.9636
-0.250 -0.0479 0.01166 0.00411 0.0047 0.9888 0.9728
0.000 0.0000 0.01167 0.00411 0.0000 0.9811 0.9811
0.250 0.0479 0.01166 0.00411 -0.0047 0.9728 0.9888
0.500 0.0955 0.01164 0.00414 -0.0093 0.9636 0.9962
1.000 0.1731 0.01161 0.00424 -0.0148 0.9357 1.0000
1.250 0.2061 0.01161 0.00435 -0.0162 0.9196 1.0000
1.500 0.2370 0.01164 0.00447 -0.0170 0.9036 1.0000
1.750 0.2660 0.01168 0.00461 -0.0173 0.8875 1.0000
2.000 0.2935 0.01173 0.00477 -0.0172 0.8706 1.0000
2.250 0.3177 0.01173 0.00488 -0.0158 0.8422 1.0000
2.500 0.3349 0.01165 0.00467 -0.0120 0.7750 1.0000
2.750 0.3506 0.01177 0.00442 -0.0081 0.6659 1.0000
3.000 0.3686 0.01224 0.00439 -0.0054 0.5292 1.0000
3.250 0.3782 0.01461 0.00482 -0.0029 0.1382 1.0000
3.500 0.3977 0.01584 0.00562 -0.0018 0.0681 1.0000
3.750 0.4191 0.01666 0.00644 -0.0008 0.0510 1.0000
4.000 0.4410 0.01743 0.00733 0.0003 0.0448 1.0000
4.250 0.4615 0.01848 0.00841 0.0015 0.0409 1.0000
4.500 0.4827 0.01966 0.00966 0.0027 0.0389 1.0000
4.750 0.5056 0.02092 0.01102 0.0038 0.0372 1.0000
5.000 0.5292 0.02205 0.01229 0.0046 0.0334 1.0000
5.250 0.5525 0.02335 0.01373 0.0053 0.0304 1.0000
5.500 0.5757 0.02542 0.01594 0.0061 0.0289 1.0000
5.750 0.5984 0.02823 0.01903 0.0070 0.0280 1.0000
6.000 0.6209 0.03056 0.02181 0.0081 0.0275 1.0000
6.250 0.6423 0.03282 0.02460 0.0094 0.0261 1.0000
6.500 0.6619 0.03545 0.02776 0.0106 0.0238 1.0000
6.750 0.6784 0.03895 0.03176 0.0119 0.0233 1.0000
7.000 0.6923 0.04284 0.03613 0.0132 0.0231 1.0000
7.250 0.7035 0.04706 0.04079 0.0142 0.0231 1.0000
7.500 0.7116 0.05158 0.04569 0.0150 0.0233 1.0000
7.750 0.7165 0.05632 0.05076 0.0154 0.0236 1.0000
8.000 0.7182 0.06118 0.05590 0.0153 0.0240 1.0000
8.250 0.7167 0.06610 0.06103 0.0146 0.0244 1.0000
8.500 0.7119 0.07109 0.06617 0.0132 0.0246 1.0000
8.750 0.7032 0.07604 0.07121 0.0113 0.0250 1.0000
9.000 0.6934 0.08152 0.07674 0.0075 0.0253 1.0000
9.250 0.6867 0.08803 0.08324 0.0019 0.0258 1.0000
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Polar data table (+)
Polar graphs
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