NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 100,000 Max Cl/Cd: 43.34 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65210-il-100000.txt Download as CSV file: xf-naca65210-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5212 0.09680 0.09186 -0.0253 1.0000 0.1107
-9.250 -0.5374 0.09234 0.08750 -0.0307 1.0000 0.1150
-9.000 -0.5656 0.08721 0.08247 -0.0380 1.0000 0.1158
-8.750 -0.5314 0.08455 0.07979 -0.0314 1.0000 0.1239
-8.500 -0.5517 0.07966 0.07500 -0.0364 1.0000 0.1276
-8.250 -0.5840 0.07589 0.07120 -0.0401 1.0000 0.1295
-8.000 -0.5685 0.07190 0.06729 -0.0381 1.0000 0.1359
-7.750 -0.5889 0.06880 0.06409 -0.0396 1.0000 0.1432
-7.500 -0.5808 0.06500 0.06037 -0.0381 1.0000 0.1501
-7.000 -0.6098 0.06131 0.05625 -0.0356 1.0000 0.1729
-5.250 -0.5405 0.03365 0.02594 -0.0228 1.0000 0.0859
-5.000 -0.5195 0.03156 0.02305 -0.0204 1.0000 0.0747
-4.750 -0.5000 0.02846 0.01977 -0.0193 1.0000 0.0725
-4.500 -0.4796 0.02672 0.01771 -0.0179 1.0000 0.0729
-4.250 -0.4588 0.02565 0.01628 -0.0166 1.0000 0.0746
-4.000 -0.4366 0.02415 0.01457 -0.0155 1.0000 0.0748
-3.750 -0.4140 0.02241 0.01275 -0.0145 1.0000 0.0760
-3.500 -0.3931 0.02111 0.01151 -0.0135 1.0000 0.0787
-3.250 -0.3731 0.02035 0.01076 -0.0124 1.0000 0.0859
-3.000 -0.3535 0.01943 0.00988 -0.0112 1.0000 0.0912
-2.750 -0.3339 0.01871 0.00921 -0.0102 1.0000 0.0992
-2.500 -0.3019 0.01789 0.00845 -0.0117 0.9963 0.1227
-2.250 -0.2895 0.01521 0.00879 -0.0081 0.9923 0.7316
-2.000 -0.2793 0.01615 0.00989 -0.0014 0.9844 0.8338
-1.750 -0.2707 0.01680 0.01054 0.0050 0.9764 0.8885
-1.500 -0.1744 0.01845 0.01187 -0.0023 0.9829 0.9644
-1.250 -0.1201 0.01849 0.01169 -0.0086 0.9790 0.9729
-1.000 -0.0654 0.01853 0.01154 -0.0151 0.9748 0.9794
-0.750 -0.0098 0.01859 0.01147 -0.0218 0.9711 0.9857
-0.500 0.0419 0.01860 0.01138 -0.0279 0.9668 0.9924
-0.250 0.0936 0.01860 0.01130 -0.0340 0.9621 0.9994
0.000 0.1343 0.01868 0.01133 -0.0380 0.9563 1.0000
0.250 0.1554 0.01874 0.01138 -0.0384 0.9466 1.0000
0.500 0.1906 0.01886 0.01149 -0.0412 0.9404 1.0000
0.750 0.2098 0.01898 0.01161 -0.0411 0.9309 1.0000
1.000 0.2302 0.01915 0.01179 -0.0411 0.9223 1.0000
1.250 0.2604 0.01931 0.01198 -0.0427 0.9152 1.0000
1.500 0.2696 0.01954 0.01224 -0.0405 0.9050 1.0000
1.750 0.3090 0.01973 0.01249 -0.0435 0.8997 1.0000
2.000 0.3130 0.02001 0.01278 -0.0403 0.8886 1.0000
2.250 0.3357 0.02030 0.01313 -0.0401 0.8803 1.0000
2.500 0.3699 0.02052 0.01346 -0.0419 0.8728 1.0000
2.750 0.3908 0.02085 0.01385 -0.0413 0.8628 1.0000
3.000 0.4417 0.02085 0.01405 -0.0454 0.8568 1.0000
3.250 0.4635 0.02113 0.01444 -0.0447 0.8453 1.0000
3.500 0.5704 0.01641 0.01010 -0.0487 0.7931 1.0000
3.750 0.5928 0.01492 0.00863 -0.0439 0.7522 1.0000
4.000 0.6077 0.01410 0.00782 -0.0391 0.7030 1.0000
4.250 0.6059 0.01398 0.00659 -0.0303 0.4343 1.0000
4.500 0.5943 0.01732 0.00784 -0.0246 0.1279 1.0000
4.750 0.6091 0.01866 0.00898 -0.0225 0.1012 1.0000
5.000 0.6262 0.01986 0.01011 -0.0208 0.0887 1.0000
5.250 0.6461 0.02116 0.01132 -0.0195 0.0815 1.0000
5.500 0.6708 0.02283 0.01292 -0.0188 0.0768 1.0000
5.750 0.6972 0.02416 0.01432 -0.0184 0.0704 1.0000
6.000 0.7266 0.02624 0.01635 -0.0185 0.0674 1.0000
6.250 0.7578 0.02912 0.01931 -0.0188 0.0662 1.0000
6.500 0.7857 0.03155 0.02202 -0.0184 0.0664 1.0000
6.750 0.8102 0.03470 0.02549 -0.0177 0.0657 1.0000
7.000 0.8316 0.03688 0.02815 -0.0164 0.0649 1.0000
7.250 0.8529 0.03954 0.03164 -0.0140 0.0710 1.0000
7.500 0.8732 0.04545 0.03776 -0.0133 0.0784 1.0000
9.500 0.7796 0.08997 0.08551 -0.0125 0.1697 1.0000
9.750 0.8003 0.09283 0.08840 -0.0094 0.1597 1.0000
10.000 0.7577 0.10091 0.09635 -0.0186 0.1550 1.0000
10.250 0.6845 0.10121 0.09702 -0.0104 0.1610 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 65-210 (naca65210-il)