NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 500,000 Max Cl/Cd: 88.84 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651412-il-500000-n5.txt Download as CSV file: xf-naca651412-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4891 0.08523 0.08289 -0.0518 1.0000 0.0096
-10.750 -0.5131 0.07544 0.07316 -0.0576 1.0000 0.0097
-10.500 -0.5940 0.05591 0.05351 -0.0711 1.0000 0.0092
-10.250 -0.6281 0.04660 0.04389 -0.0770 0.9807 0.0094
-10.000 -0.6801 0.02732 0.02307 -0.0814 0.9557 0.0106
-9.750 -0.6622 0.02413 0.01935 -0.0820 0.9462 0.0111
-9.500 -0.6395 0.02287 0.01793 -0.0825 0.9370 0.0116
-9.250 -0.6159 0.02221 0.01716 -0.0826 0.9277 0.0118
-9.000 -0.5915 0.02176 0.01663 -0.0827 0.9193 0.0122
-8.750 -0.5697 0.02096 0.01567 -0.0823 0.9099 0.0127
-8.500 -0.5480 0.01988 0.01438 -0.0818 0.9015 0.0132
-8.250 -0.5261 0.01877 0.01305 -0.0812 0.8930 0.0137
-8.000 -0.5033 0.01787 0.01196 -0.0807 0.8854 0.0143
-7.750 -0.4796 0.01718 0.01109 -0.0803 0.8774 0.0147
-7.500 -0.4570 0.01630 0.01011 -0.0799 0.8699 0.0154
-7.250 -0.4325 0.01586 0.00962 -0.0796 0.8625 0.0159
-7.000 -0.4079 0.01536 0.00903 -0.0794 0.8556 0.0165
-6.750 -0.3835 0.01480 0.00838 -0.0790 0.8484 0.0170
-6.500 -0.3588 0.01428 0.00776 -0.0787 0.8416 0.0177
-6.250 -0.3338 0.01381 0.00719 -0.0784 0.8345 0.0184
-6.000 -0.3083 0.01345 0.00673 -0.0782 0.8284 0.0190
-5.750 -0.2840 0.01283 0.00605 -0.0779 0.8218 0.0197
-5.500 -0.2592 0.01233 0.00549 -0.0776 0.8156 0.0205
-5.250 -0.2335 0.01195 0.00508 -0.0775 0.8093 0.0213
-5.000 -0.2075 0.01163 0.00469 -0.0774 0.8029 0.0221
-4.750 -0.1813 0.01132 0.00432 -0.0773 0.7972 0.0231
-4.500 -0.1546 0.01106 0.00402 -0.0773 0.7913 0.0244
-4.250 -0.1278 0.01084 0.00373 -0.0773 0.7858 0.0253
-4.000 -0.1014 0.01045 0.00329 -0.0773 0.7802 0.0271
-3.750 -0.0744 0.01020 0.00302 -0.0773 0.7742 0.0290
-3.500 -0.0471 0.01002 0.00278 -0.0774 0.7690 0.0312
-3.250 -0.0195 0.00986 0.00258 -0.0775 0.7634 0.0336
-3.000 0.0079 0.00965 0.00236 -0.0776 0.7582 0.0402
-2.750 0.0355 0.00946 0.00219 -0.0777 0.7534 0.0518
-2.500 0.0627 0.00910 0.00201 -0.0779 0.7480 0.1063
-2.250 0.0888 0.00836 0.00177 -0.0784 0.7427 0.2579
-2.000 0.1145 0.00737 0.00154 -0.0790 0.7381 0.4857
-1.750 0.1417 0.00705 0.00159 -0.0791 0.7331 0.5992
-1.500 0.1693 0.00700 0.00165 -0.0791 0.7282 0.6478
-1.250 0.1975 0.00702 0.00166 -0.0792 0.7237 0.6666
-1.000 0.2257 0.00702 0.00168 -0.0793 0.7189 0.6813
-0.750 0.2541 0.00703 0.00167 -0.0794 0.7142 0.6880
-0.250 0.3112 0.00708 0.00166 -0.0799 0.7053 0.6980
0.000 0.3396 0.00709 0.00167 -0.0801 0.7006 0.7024
0.250 0.3679 0.00712 0.00169 -0.0802 0.6963 0.7074
0.500 0.3964 0.00715 0.00171 -0.0805 0.6920 0.7125
0.750 0.4248 0.00717 0.00175 -0.0807 0.6874 0.7173
1.000 0.4531 0.00721 0.00180 -0.0808 0.6831 0.7222
1.250 0.4814 0.00726 0.00184 -0.0810 0.6791 0.7275
1.500 0.5098 0.00728 0.00192 -0.0812 0.6746 0.7324
1.750 0.5380 0.00732 0.00199 -0.0813 0.6700 0.7377
2.250 0.5938 0.00742 0.00214 -0.0815 0.6563 0.7482
2.500 0.6206 0.00747 0.00219 -0.0813 0.6422 0.7539
2.750 0.6475 0.00755 0.00226 -0.0812 0.6273 0.7600
3.000 0.6731 0.00766 0.00233 -0.0808 0.6047 0.7654
3.250 0.6974 0.00785 0.00242 -0.0801 0.5653 0.7714
3.500 0.7201 0.00818 0.00256 -0.0792 0.5117 0.7774
3.750 0.7345 0.00914 0.00296 -0.0771 0.3891 0.7841
4.250 0.7649 0.01125 0.00409 -0.0734 0.1714 0.7982
4.500 0.7820 0.01214 0.00462 -0.0720 0.0922 0.8057
4.750 0.8016 0.01276 0.00506 -0.0708 0.0501 0.8125
5.000 0.8239 0.01319 0.00544 -0.0700 0.0365 0.8203
5.250 0.8468 0.01351 0.00580 -0.0692 0.0312 0.8279
5.500 0.8690 0.01390 0.00620 -0.0684 0.0267 0.8364
5.750 0.8913 0.01421 0.00658 -0.0676 0.0244 0.8444
6.000 0.9133 0.01456 0.00699 -0.0667 0.0223 0.8530
6.250 0.9335 0.01498 0.00745 -0.0655 0.0204 0.8622
6.500 0.9528 0.01543 0.00796 -0.0641 0.0190 0.8723
6.750 0.9724 0.01582 0.00843 -0.0628 0.0181 0.8834
7.000 0.9907 0.01624 0.00893 -0.0612 0.0172 0.8957
7.250 1.0075 0.01666 0.00943 -0.0594 0.0164 0.9094
8.000 1.0481 0.01839 0.01135 -0.0526 0.0146 1.0000
8.250 1.0645 0.01905 0.01208 -0.0512 0.0144 1.0000
8.500 1.0807 0.01975 0.01284 -0.0497 0.0140 1.0000
8.750 1.0963 0.02048 0.01363 -0.0482 0.0137 1.0000
9.000 1.1117 0.02125 0.01446 -0.0468 0.0133 1.0000
9.250 1.1264 0.02209 0.01536 -0.0453 0.0129 1.0000
9.500 1.1408 0.02298 0.01631 -0.0439 0.0126 1.0000
9.750 1.1551 0.02389 0.01730 -0.0425 0.0124 1.0000
10.000 1.1691 0.02486 0.01833 -0.0411 0.0121 1.0000
10.250 1.1829 0.02587 0.01941 -0.0398 0.0119 1.0000
10.500 1.1964 0.02691 0.02051 -0.0385 0.0117 1.0000
10.750 1.2091 0.02807 0.02174 -0.0372 0.0115 1.0000
11.000 1.2213 0.02935 0.02310 -0.0359 0.0113 1.0000
11.250 1.2322 0.03086 0.02471 -0.0346 0.0111 1.0000
11.500 1.2430 0.03250 0.02647 -0.0333 0.0109 1.0000
11.750 1.2550 0.03384 0.02794 -0.0322 0.0107 1.0000
12.000 1.2659 0.03529 0.02953 -0.0311 0.0105 1.0000
12.250 1.2757 0.03689 0.03128 -0.0300 0.0103 1.0000
12.500 1.2841 0.03866 0.03321 -0.0288 0.0101 1.0000
12.750 1.2911 0.04060 0.03530 -0.0277 0.0100 1.0000
13.000 1.2964 0.04270 0.03757 -0.0267 0.0098 1.0000
13.250 1.2996 0.04508 0.04013 -0.0257 0.0096 1.0000
13.500 1.3014 0.04756 0.04280 -0.0248 0.0095 1.0000
13.750 1.3013 0.05032 0.04574 -0.0241 0.0094 1.0000
14.000 1.2994 0.05330 0.04890 -0.0235 0.0092 1.0000
14.250 1.2968 0.05638 0.05214 -0.0232 0.0091 1.0000
14.500 1.2934 0.05966 0.05557 -0.0233 0.0090 1.0000
14.750 1.2884 0.06325 0.05932 -0.0236 0.0089 1.0000
15.000 1.2822 0.06717 0.06339 -0.0242 0.0088 1.0000
15.250 1.2765 0.07120 0.06756 -0.0252 0.0087 1.0000
15.500 1.2703 0.07549 0.07198 -0.0265 0.0086 1.0000
15.750 1.2603 0.08066 0.07730 -0.0284 0.0085 1.0000
16.000 1.2473 0.08665 0.08347 -0.0310 0.0085 1.0000
16.250 1.2345 0.09299 0.08996 -0.0340 0.0084 1.0000
16.500 1.2183 0.10040 0.09753 -0.0380 0.0084 1.0000
16.750 1.1873 0.11173 0.10914 -0.0446 0.0084 1.0000
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Polar data table (+)
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