NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-012A AIRFOIL (n64012a-il) Reynolds number: 1,000,000 Max Cl/Cd: 61.91 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64012a-il-1000000.txt Download as CSV file: xf-n64012a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-012A 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9398 0.10817 0.10633 0.0037 1.0000 0.0098
-15.500 -0.9636 0.09691 0.09493 -0.0032 1.0000 0.0097
-15.250 -0.9799 0.08825 0.08615 -0.0088 1.0000 0.0096
-15.000 -0.9972 0.08028 0.07806 -0.0140 1.0000 0.0096
-14.750 -1.0140 0.07316 0.07080 -0.0185 1.0000 0.0096
-14.500 -1.0341 0.06620 0.06369 -0.0225 1.0000 0.0096
-14.250 -1.0565 0.05948 0.05678 -0.0259 1.0000 0.0096
-14.000 -1.0802 0.05319 0.05026 -0.0283 1.0000 0.0096
-13.750 -1.1057 0.04720 0.04403 -0.0297 1.0000 0.0096
-13.500 -1.1308 0.04171 0.03825 -0.0298 1.0000 0.0097
-13.250 -1.1466 0.03757 0.03387 -0.0289 1.0000 0.0098
-13.000 -1.1524 0.03470 0.03082 -0.0276 1.0000 0.0100
-12.750 -1.1511 0.03271 0.02871 -0.0262 1.0000 0.0101
-12.500 -1.1461 0.03117 0.02707 -0.0248 1.0000 0.0103
-12.250 -1.1387 0.02992 0.02573 -0.0232 1.0000 0.0104
-12.000 -1.1301 0.02879 0.02451 -0.0215 1.0000 0.0106
-11.750 -1.1205 0.02771 0.02334 -0.0196 1.0000 0.0108
-11.500 -1.1093 0.02665 0.02216 -0.0179 1.0000 0.0110
-11.250 -1.0950 0.02557 0.02098 -0.0165 1.0000 0.0112
-11.000 -1.0795 0.02450 0.01979 -0.0153 1.0000 0.0115
-10.750 -1.0625 0.02353 0.01872 -0.0142 1.0000 0.0118
-10.500 -1.0442 0.02270 0.01779 -0.0131 1.0000 0.0121
-10.250 -1.0250 0.02194 0.01693 -0.0122 1.0000 0.0124
-10.000 -1.0052 0.02120 0.01609 -0.0113 1.0000 0.0125
-9.750 -0.9846 0.02056 0.01537 -0.0104 1.0000 0.0127
-9.500 -0.9725 0.01836 0.01299 -0.0085 1.0000 0.0131
-9.250 -0.9550 0.01734 0.01191 -0.0072 1.0000 0.0135
-9.000 -0.9352 0.01667 0.01122 -0.0061 1.0000 0.0139
-8.750 -0.9149 0.01612 0.01063 -0.0050 1.0000 0.0143
-8.500 -0.8951 0.01558 0.01006 -0.0038 1.0000 0.0147
-8.250 -0.8755 0.01510 0.00955 -0.0025 1.0000 0.0152
-8.000 -0.8564 0.01467 0.00907 -0.0011 1.0000 0.0156
-7.750 -0.8381 0.01422 0.00859 0.0005 1.0000 0.0160
-7.500 -0.8202 0.01380 0.00813 0.0022 0.9999 0.0163
-7.250 -0.7874 0.01315 0.00743 0.0007 0.9971 0.0167
-7.000 -0.7558 0.01221 0.00641 -0.0008 0.9939 0.0178
-6.750 -0.7235 0.01174 0.00594 -0.0022 0.9894 0.0188
-6.500 -0.6897 0.01134 0.00552 -0.0038 0.9849 0.0199
-6.250 -0.6579 0.01101 0.00516 -0.0049 0.9777 0.0210
-6.000 -0.6262 0.01053 0.00463 -0.0060 0.9699 0.0228
-5.750 -0.5980 0.01017 0.00426 -0.0063 0.9575 0.0251
-5.500 -0.5709 0.00993 0.00398 -0.0062 0.9431 0.0273
-5.250 -0.5464 0.00958 0.00361 -0.0056 0.9269 0.0326
-5.000 -0.5216 0.00932 0.00332 -0.0050 0.9109 0.0396
-4.750 -0.4968 0.00906 0.00307 -0.0044 0.8953 0.0512
-4.500 -0.4719 0.00877 0.00282 -0.0040 0.8804 0.0714
-4.250 -0.4476 0.00840 0.00256 -0.0035 0.8665 0.1087
-4.000 -0.4242 0.00788 0.00228 -0.0029 0.8534 0.1741
-3.750 -0.4020 0.00721 0.00197 -0.0022 0.8409 0.2707
-3.500 -0.3816 0.00637 0.00163 -0.0012 0.8292 0.4068
-3.250 -0.3576 0.00599 0.00149 -0.0007 0.8185 0.4865
-3.000 -0.3314 0.00581 0.00141 -0.0004 0.8083 0.5268
-2.750 -0.3043 0.00572 0.00134 -0.0003 0.7989 0.5502
-2.500 -0.2772 0.00565 0.00127 -0.0001 0.7894 0.5691
-2.250 -0.2497 0.00559 0.00123 -0.0001 0.7800 0.5874
-2.000 -0.2224 0.00555 0.00118 0.0000 0.7712 0.6054
-1.750 -0.1950 0.00549 0.00115 0.0001 0.7623 0.6248
-1.500 -0.1676 0.00544 0.00114 0.0002 0.7541 0.6432
-1.250 -0.1400 0.00542 0.00112 0.0002 0.7455 0.6567
-1.000 -0.1120 0.00541 0.00110 0.0002 0.7371 0.6688
-0.750 -0.0843 0.00540 0.00108 0.0002 0.7287 0.6799
-0.500 -0.0562 0.00538 0.00107 0.0001 0.7205 0.6885
-0.250 -0.0282 0.00540 0.00106 0.0001 0.7127 0.6966
0.000 0.0000 0.00537 0.00106 0.0000 0.7044 0.7044
0.250 0.0281 0.00540 0.00106 -0.0001 0.6966 0.7127
0.500 0.0562 0.00538 0.00107 -0.0001 0.6884 0.7205
0.750 0.0843 0.00540 0.00108 -0.0002 0.6799 0.7287
1.000 0.1119 0.00541 0.00110 -0.0002 0.6688 0.7371
1.250 0.1399 0.00542 0.00112 -0.0002 0.6568 0.7455
1.500 0.1676 0.00544 0.00114 -0.0002 0.6432 0.7541
1.750 0.1949 0.00549 0.00115 -0.0001 0.6249 0.7623
2.000 0.2223 0.00555 0.00118 0.0000 0.6054 0.7712
2.250 0.2497 0.00559 0.00123 0.0001 0.5874 0.7800
2.500 0.2772 0.00565 0.00127 0.0002 0.5692 0.7894
2.750 0.3043 0.00572 0.00134 0.0003 0.5502 0.7989
3.000 0.3314 0.00581 0.00141 0.0004 0.5267 0.8083
3.250 0.3575 0.00599 0.00149 0.0007 0.4862 0.8185
3.500 0.3817 0.00636 0.00163 0.0012 0.4078 0.8292
3.750 0.4021 0.00721 0.00197 0.0022 0.2710 0.8409
4.000 0.4243 0.00788 0.00228 0.0029 0.1742 0.8534
4.250 0.4477 0.00840 0.00256 0.0034 0.1088 0.8665
4.500 0.4720 0.00877 0.00282 0.0039 0.0715 0.8805
4.750 0.4969 0.00906 0.00307 0.0044 0.0512 0.8953
5.000 0.5217 0.00932 0.00333 0.0050 0.0396 0.9109
5.250 0.5465 0.00958 0.00361 0.0055 0.0326 0.9269
5.500 0.5711 0.00993 0.00398 0.0061 0.0272 0.9430
5.750 0.5981 0.01017 0.00426 0.0062 0.0251 0.9575
6.000 0.6262 0.01053 0.00463 0.0060 0.0227 0.9700
6.250 0.6580 0.01101 0.00515 0.0049 0.0209 0.9778
6.500 0.6898 0.01134 0.00552 0.0037 0.0199 0.9849
6.750 0.7235 0.01174 0.00594 0.0021 0.0188 0.9894
7.000 0.7559 0.01221 0.00641 0.0008 0.0178 0.9940
7.250 0.7874 0.01318 0.00745 -0.0007 0.0167 0.9972
7.500 0.8204 0.01380 0.00813 -0.0023 0.0163 1.0000
7.750 0.8379 0.01422 0.00859 -0.0005 0.0160 1.0000
8.000 0.8563 0.01466 0.00907 0.0011 0.0156 1.0000
8.250 0.8754 0.01510 0.00955 0.0026 0.0152 1.0000
8.500 0.8951 0.01558 0.01006 0.0038 0.0147 1.0000
8.750 0.9151 0.01611 0.01062 0.0050 0.0143 1.0000
9.000 0.9354 0.01668 0.01122 0.0060 0.0139 1.0000
9.250 0.9553 0.01734 0.01192 0.0071 0.0135 1.0000
9.500 0.9728 0.01838 0.01302 0.0084 0.0131 1.0000
9.750 0.9851 0.02056 0.01537 0.0103 0.0127 1.0000
10.000 1.0058 0.02120 0.01610 0.0112 0.0125 1.0000
10.250 1.0256 0.02195 0.01694 0.0121 0.0124 1.0000
10.500 1.0449 0.02271 0.01780 0.0130 0.0121 1.0000
10.750 1.0633 0.02354 0.01873 0.0140 0.0118 1.0000
11.000 1.0803 0.02451 0.01981 0.0151 0.0115 1.0000
11.250 1.0959 0.02558 0.02099 0.0163 0.0112 1.0000
11.500 1.1103 0.02665 0.02216 0.0177 0.0110 1.0000
11.750 1.1216 0.02773 0.02335 0.0194 0.0108 1.0000
12.000 1.1314 0.02880 0.02452 0.0212 0.0106 1.0000
12.250 1.1401 0.02991 0.02573 0.0229 0.0104 1.0000
12.500 1.1473 0.03119 0.02709 0.0245 0.0103 1.0000
12.750 1.1524 0.03273 0.02873 0.0260 0.0101 1.0000
13.000 1.1536 0.03475 0.03087 0.0273 0.0100 1.0000
13.250 1.1473 0.03769 0.03399 0.0286 0.0098 1.0000
13.500 1.1306 0.04194 0.03850 0.0295 0.0097 1.0000
13.750 1.1067 0.04731 0.04414 0.0294 0.0096 1.0000
14.000 1.0791 0.05361 0.05070 0.0279 0.0096 1.0000
14.250 1.0557 0.05990 0.05721 0.0254 0.0096 1.0000
14.500 1.0335 0.06665 0.06415 0.0219 0.0095 1.0000
14.750 1.0139 0.07359 0.07125 0.0178 0.0096 1.0000
15.000 0.9968 0.08083 0.07862 0.0133 0.0096 1.0000
15.250 0.9809 0.08859 0.08650 0.0082 0.0096 1.0000
15.500 0.9644 0.09733 0.09536 0.0025 0.0097 1.0000
15.750 0.9388 0.10916 0.10734 -0.0047 0.0098 1.0000
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