NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 50,000 Max Cl/Cd: 22.19 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65206-il-50000.txt Download as CSV file: xf-naca65206-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-206
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 -0.5589 0.10390 0.09710 0.0010 1.0000 0.2108
-8.250 -0.5555 0.10059 0.09384 0.0010 1.0000 0.2262
-8.000 -0.5571 0.09777 0.09111 0.0007 1.0000 0.2430
-7.750 -0.5495 0.09420 0.08759 0.0022 1.0000 0.2680
-7.500 -0.5441 0.09096 0.08440 0.0037 1.0000 0.2941
-7.250 -0.5394 0.08794 0.08144 0.0053 1.0000 0.3220
-7.000 -0.5424 0.08556 0.07917 0.0071 1.0000 0.3517
-6.750 -0.5297 0.08226 0.07588 0.0104 1.0000 0.3917
-6.500 -0.5090 0.07862 0.07224 0.0145 1.0000 0.4444
-6.250 -0.4996 0.07613 0.06980 0.0190 1.0000 0.5001
-6.000 -0.4550 0.07107 0.06454 0.0228 1.0000 0.5778
-5.750 -0.4222 0.06672 0.06016 0.0248 1.0000 0.6432
-5.000 -0.4023 0.05771 0.05132 0.0261 1.0000 0.6781
-4.500 -0.4080 0.03933 0.03083 -0.0360 1.0000 0.1629
-4.250 -0.3772 0.03552 0.02632 -0.0362 1.0000 0.1336
-4.000 -0.3486 0.03236 0.02242 -0.0356 1.0000 0.1183
-3.750 -0.3198 0.03008 0.01936 -0.0347 1.0000 0.1107
-3.500 -0.2956 0.02750 0.01665 -0.0339 1.0000 0.1166
-3.250 -0.2691 0.02545 0.01424 -0.0328 1.0000 0.1172
-3.000 -0.2428 0.02360 0.01214 -0.0313 1.0000 0.1177
-2.750 -0.2177 0.02205 0.01042 -0.0294 1.0000 0.1217
-2.500 -0.1941 0.02062 0.00891 -0.0277 1.0000 0.1300
-2.250 -0.1720 0.01928 0.00765 -0.0265 1.0000 0.1590
-2.000 -0.1226 0.01476 0.00614 -0.0245 1.0000 1.0000
-1.750 -0.1088 0.01465 0.00548 -0.0222 1.0000 1.0000
-1.500 -0.0931 0.01458 0.00502 -0.0205 1.0000 1.0000
-1.250 -0.0754 0.01456 0.00467 -0.0192 1.0000 1.0000
-1.000 -0.0562 0.01456 0.00440 -0.0181 1.0000 1.0000
-0.750 -0.0361 0.01461 0.00421 -0.0173 1.0000 1.0000
-0.500 -0.0155 0.01468 0.00408 -0.0165 1.0000 1.0000
-0.250 0.0055 0.01478 0.00397 -0.0159 1.0000 1.0000
0.000 0.0267 0.01491 0.00396 -0.0153 1.0000 1.0000
0.250 0.0480 0.01506 0.00401 -0.0147 1.0000 1.0000
0.500 0.0693 0.01525 0.00411 -0.0142 1.0000 1.0000
0.750 0.0906 0.01546 0.00428 -0.0137 1.0000 1.0000
1.000 0.1118 0.01571 0.00450 -0.0133 1.0000 1.0000
1.250 0.1329 0.01598 0.00481 -0.0129 1.0000 1.0000
1.500 0.1538 0.01629 0.00514 -0.0125 1.0000 1.0000
1.750 0.1746 0.01663 0.00552 -0.0121 1.0000 1.0000
2.000 0.1952 0.01700 0.00597 -0.0118 1.0000 1.0000
2.250 0.2156 0.01741 0.00649 -0.0115 1.0000 1.0000
2.500 0.2358 0.01787 0.00708 -0.0113 1.0000 1.0000
2.750 0.2557 0.01836 0.00774 -0.0110 1.0000 1.0000
3.000 0.2754 0.01891 0.00857 -0.0108 1.0000 1.0000
3.250 0.2948 0.01951 0.00940 -0.0107 1.0000 1.0000
3.500 0.3138 0.02016 0.01032 -0.0105 1.0000 1.0000
3.750 0.3325 0.02088 0.01135 -0.0105 1.0000 1.0000
4.000 0.5350 0.02411 0.01225 -0.0217 0.1248 1.0000
4.250 0.5681 0.02637 0.01448 -0.0212 0.1144 1.0000
4.500 0.5981 0.02855 0.01680 -0.0207 0.1022 1.0000
4.750 0.6290 0.03142 0.01994 -0.0200 0.1014 1.0000
5.000 0.6586 0.03404 0.02329 -0.0188 0.1049 1.0000
5.250 0.6861 0.03756 0.02734 -0.0177 0.1109 1.0000
5.500 0.7126 0.04113 0.03170 -0.0164 0.1223 1.0000
5.750 0.7379 0.04556 0.03671 -0.0156 0.1385 1.0000
6.000 0.7628 0.05038 0.04266 -0.0155 0.1744 1.0000
6.250 0.7852 0.06263 0.05665 -0.0321 0.3412 1.0000
6.500 0.7374 0.07325 0.06735 -0.0528 0.4363 1.0000
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Polar data table (+)
Polar graphs
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