NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 50,000 Max Cl/Cd: 26.21 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212-il-50000.txt Download as CSV file: xf-naca651212-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4521 0.11019 0.10301 -0.0106 1.0000 0.3653
-9.500 -0.4512 0.10748 0.10035 -0.0102 1.0000 0.3809
-9.250 -0.4499 0.10473 0.09766 -0.0097 1.0000 0.3962
-9.000 -0.4219 0.09947 0.09234 -0.0100 1.0000 0.4051
-8.750 -0.4179 0.09624 0.08916 -0.0099 1.0000 0.4160
-8.500 -0.4280 0.07328 0.06699 -0.0340 1.0000 0.2369
-8.250 -0.4872 0.06396 0.05787 -0.0404 1.0000 0.2073
-8.000 -0.5279 0.05897 0.05298 -0.0399 1.0000 0.1946
-7.750 -0.6286 0.06463 0.05804 -0.0380 1.0000 0.1836
-7.500 -0.6480 0.06004 0.05317 -0.0364 1.0000 0.1651
-7.250 -0.6578 0.05630 0.04908 -0.0339 1.0000 0.1535
-7.000 -0.6662 0.05296 0.04515 -0.0310 1.0000 0.1430
-6.750 -0.6609 0.04968 0.04168 -0.0288 1.0000 0.1396
-6.500 -0.6575 0.04643 0.03790 -0.0264 1.0000 0.1336
-6.250 -0.6480 0.04388 0.03474 -0.0240 1.0000 0.1286
-6.000 -0.6345 0.04107 0.03165 -0.0223 1.0000 0.1261
-5.750 -0.6190 0.03855 0.02876 -0.0206 1.0000 0.1241
-5.500 -0.6015 0.03631 0.02615 -0.0189 1.0000 0.1238
-5.250 -0.5832 0.03451 0.02396 -0.0174 1.0000 0.1263
-5.000 -0.5633 0.03292 0.02196 -0.0159 1.0000 0.1294
-4.750 -0.5411 0.03116 0.02003 -0.0147 1.0000 0.1317
-4.500 -0.5179 0.02966 0.01856 -0.0134 1.0000 0.1362
-4.250 -0.4959 0.02869 0.01741 -0.0118 1.0000 0.1446
-4.000 -0.4758 0.02756 0.01640 -0.0101 1.0000 0.1565
-3.750 -0.4581 0.02648 0.01541 -0.0081 1.0000 0.1697
-3.500 -0.1554 0.03011 0.02107 -0.0228 1.0000 0.9709
-3.250 -0.0937 0.02879 0.01937 -0.0314 1.0000 0.9895
-3.000 -0.0577 0.02805 0.01840 -0.0356 1.0000 1.0000
-2.750 -0.0614 0.02806 0.01837 -0.0324 1.0000 1.0000
-2.500 -0.0647 0.02807 0.01830 -0.0293 1.0000 1.0000
-2.250 -0.0676 0.02805 0.01823 -0.0263 1.0000 1.0000
-2.000 -0.0700 0.02801 0.01814 -0.0233 1.0000 1.0000
-1.750 -0.0721 0.02796 0.01803 -0.0204 1.0000 1.0000
-1.500 -0.0740 0.02788 0.01790 -0.0175 1.0000 1.0000
-1.250 -0.0758 0.02779 0.01775 -0.0146 1.0000 1.0000
-1.000 -0.0776 0.02767 0.01758 -0.0117 1.0000 1.0000
-0.750 -0.0795 0.02752 0.01740 -0.0088 1.0000 1.0000
-0.500 -0.0816 0.02735 0.01716 -0.0058 1.0000 1.0000
-0.250 -0.0840 0.02714 0.01691 -0.0028 1.0000 1.0000
0.000 -0.0868 0.02689 0.01662 0.0003 1.0000 1.0000
0.250 -0.0899 0.02661 0.01629 0.0035 1.0000 1.0000
0.500 -0.0929 0.02629 0.01593 0.0067 1.0000 1.0000
0.750 -0.0945 0.02599 0.01558 0.0097 1.0000 1.0000
1.000 -0.0923 0.02579 0.01532 0.0122 1.0000 1.0000
1.250 -0.0832 0.02580 0.01525 0.0135 1.0000 1.0000
1.500 -0.0693 0.02600 0.01537 0.0139 1.0000 1.0000
1.750 -0.0525 0.02634 0.01564 0.0140 1.0000 1.0000
2.000 -0.0344 0.02677 0.01602 0.0138 1.0000 1.0000
2.250 -0.0155 0.02728 0.01648 0.0135 1.0000 1.0000
2.500 0.0037 0.02787 0.01703 0.0131 1.0000 1.0000
2.750 0.0230 0.02850 0.01765 0.0128 1.0000 1.0000
3.000 0.0422 0.02920 0.01833 0.0124 1.0000 1.0000
3.250 0.0835 0.03076 0.01996 0.0077 0.9888 1.0000
3.500 0.1224 0.03228 0.02153 0.0035 0.9772 1.0000
3.750 0.1599 0.03376 0.02310 -0.0003 0.9646 1.0000
4.000 0.1965 0.03523 0.02469 -0.0038 0.9511 1.0000
4.250 0.2321 0.03666 0.02624 -0.0070 0.9364 1.0000
4.500 0.2676 0.03807 0.02781 -0.0101 0.9197 1.0000
4.750 0.3061 0.03954 0.02949 -0.0135 0.9014 1.0000
5.000 0.3460 0.04098 0.03114 -0.0167 0.8804 1.0000
5.250 0.3801 0.04215 0.03255 -0.0188 0.8581 1.0000
5.500 0.4208 0.04331 0.03402 -0.0214 0.8328 1.0000
5.750 0.4663 0.04410 0.03517 -0.0239 0.8028 1.0000
6.000 0.6637 0.02532 0.01521 -0.0089 0.2374 1.0000
6.250 0.6642 0.02773 0.01694 -0.0053 0.1880 1.0000
6.500 0.6826 0.02961 0.01850 -0.0036 0.1592 1.0000
6.750 0.7306 0.03159 0.02040 -0.0051 0.1389 1.0000
7.000 0.7797 0.03393 0.02270 -0.0072 0.1250 1.0000
7.250 0.8258 0.03716 0.02589 -0.0093 0.1194 1.0000
7.500 0.8528 0.03959 0.02881 -0.0086 0.1168 1.0000
7.750 0.8755 0.04220 0.03184 -0.0077 0.1135 1.0000
8.000 0.8959 0.04519 0.03524 -0.0066 0.1121 1.0000
8.250 0.9127 0.04864 0.03916 -0.0052 0.1135 1.0000
8.500 0.9258 0.05236 0.04331 -0.0037 0.1157 1.0000
8.750 0.9388 0.05656 0.04785 -0.0025 0.1182 1.0000
9.000 0.9392 0.06011 0.05201 -0.0001 0.1225 1.0000
9.250 0.9269 0.06456 0.05702 0.0025 0.1279 1.0000
9.500 0.9282 0.06933 0.06199 0.0036 0.1317 1.0000
9.750 0.8982 0.07363 0.06674 0.0058 0.1386 1.0000
10.000 0.8737 0.07855 0.07183 0.0070 0.1442 1.0000
10.250 0.8401 0.08397 0.07735 0.0065 0.1513 1.0000
10.500 0.7895 0.09194 0.08534 0.0019 0.1569 1.0000
10.750 0.7639 0.10516 0.09856 -0.0069 0.1904 1.0000
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Polar data table (+)
Polar graphs
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