NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(3)-418 (naca663418-il) Reynolds number: 200,000 Max Cl/Cd: 42.68 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca663418-il-200000.txt Download as CSV file: xf-naca663418-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-418
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.1454 0.10127 0.09747 -0.1184 0.9359 0.0841
-13.250 -0.1370 0.09866 0.09485 -0.1191 0.9325 0.0861
-13.000 -0.2655 0.09690 0.09303 -0.1222 0.9575 0.0838
-12.750 -0.2499 0.09479 0.09090 -0.1231 0.9529 0.0860
-12.500 -0.1927 0.07888 0.07511 -0.1295 0.9255 0.0961
-12.250 -0.1729 0.07849 0.07470 -0.1276 0.9214 0.0979
-12.000 -0.1732 0.07481 0.07100 -0.1284 0.9181 0.1000
-11.750 -0.2126 0.06503 0.06122 -0.1339 0.9155 0.1030
-11.500 -0.2681 0.05646 0.05253 -0.1371 0.9123 0.1035
-11.250 -0.3113 0.05146 0.04742 -0.1367 0.9075 0.1041
-11.000 -0.3481 0.04805 0.04387 -0.1344 0.9017 0.1048
-10.750 -0.3927 0.04606 0.04166 -0.1297 0.8960 0.1062
-10.500 -0.5647 0.04785 0.04160 -0.1134 0.8912 0.0592
-10.250 -0.5833 0.04253 0.03558 -0.1072 0.8858 0.0509
-10.000 -0.5610 0.03936 0.03228 -0.1074 0.8835 0.0500
-9.750 -0.5458 0.03705 0.02973 -0.1062 0.8811 0.0495
-9.500 -0.5290 0.03524 0.02765 -0.1050 0.8791 0.0496
-9.250 -0.5141 0.03411 0.02626 -0.1033 0.8770 0.0501
-9.000 -0.5102 0.03367 0.02565 -0.0998 0.8723 0.0504
-8.750 -0.4968 0.03287 0.02466 -0.0978 0.8691 0.0507
-8.500 -0.4591 0.03067 0.02231 -0.0999 0.8681 0.0512
-8.250 -0.4047 0.02853 0.02017 -0.1049 0.8681 0.0525
-8.000 -0.3594 0.02729 0.01892 -0.1083 0.8674 0.0543
-7.750 -0.3288 0.02664 0.01824 -0.1091 0.8658 0.0566
-7.500 -0.2985 0.02605 0.01757 -0.1096 0.8643 0.0586
-7.250 -0.2642 0.02520 0.01674 -0.1108 0.8633 0.0608
-7.000 -0.2429 0.02463 0.01625 -0.1100 0.8619 0.0635
-6.750 -0.2251 0.02427 0.01588 -0.1088 0.8604 0.0666
-6.500 -0.2456 0.02525 0.01687 -0.1013 0.8547 0.0673
-6.250 -0.2622 0.02590 0.01751 -0.0941 0.8503 0.0683
-6.000 -0.2656 0.02593 0.01751 -0.0891 0.8474 0.0706
-5.750 -0.2643 0.02564 0.01726 -0.0850 0.8452 0.0742
-5.500 -0.3947 0.02925 0.02076 -0.0573 0.8364 0.0654
-5.250 -0.4078 0.02961 0.02109 -0.0508 0.8344 0.0667
-5.000 -0.4082 0.02972 0.02116 -0.0464 0.8329 0.0688
-4.750 -0.4004 0.02931 0.02078 -0.0435 0.8310 0.0728
-4.500 -0.3924 0.02922 0.02070 -0.0407 0.8301 0.0779
-4.250 -0.3764 0.02888 0.02036 -0.0392 0.8289 0.0854
-4.000 -0.3550 0.02807 0.01978 -0.0387 0.8275 0.1206
-3.750 -0.3606 0.02504 0.01877 -0.0352 0.8264 0.4855
-3.500 -0.3791 0.02565 0.02021 -0.0269 0.8239 0.6534
-3.250 -0.3788 0.02651 0.02108 -0.0221 0.8220 0.6962
-3.000 -0.3699 0.02726 0.02176 -0.0189 0.8196 0.7218
-2.750 -0.3563 0.02812 0.02258 -0.0162 0.8176 0.7391
-2.500 -0.3405 0.02910 0.02357 -0.0133 0.8157 0.7524
-2.250 -0.3166 0.03010 0.02457 -0.0112 0.8130 0.7662
-2.000 -0.2894 0.03159 0.02607 -0.0084 0.8107 0.7851
-1.750 -0.2595 0.03357 0.02805 -0.0049 0.8091 0.8096
-1.500 -0.2940 0.03393 0.02848 0.0053 0.8024 0.8149
-1.250 -0.2851 0.03499 0.02954 0.0106 0.7991 0.8307
-1.000 -0.2593 0.03537 0.02983 0.0112 0.7961 0.8425
-0.750 -0.2175 0.03554 0.02992 0.0094 0.7937 0.8450
-0.500 -0.2205 0.03567 0.03004 0.0142 0.7868 0.8491
-0.250 -0.2027 0.03562 0.02994 0.0152 0.7821 0.8526
0.000 -0.1700 0.03552 0.02975 0.0137 0.7791 0.8551
0.250 -0.1302 0.03544 0.02959 0.0110 0.7771 0.8571
0.500 -0.0868 0.03546 0.02953 0.0077 0.7758 0.8586
0.750 -0.1052 0.03535 0.02943 0.0141 0.7645 0.8617
1.000 -0.0704 0.03531 0.02935 0.0127 0.7620 0.8629
1.250 -0.0305 0.03527 0.02925 0.0103 0.7603 0.8637
1.500 0.0127 0.03526 0.02920 0.0074 0.7591 0.8644
1.750 0.0000 0.03535 0.02930 0.0126 0.7468 0.8675
2.000 0.0388 0.03523 0.02916 0.0103 0.7448 0.8682
2.250 0.0793 0.03517 0.02907 0.0077 0.7434 0.8689
2.500 0.0780 0.03545 0.02936 0.0108 0.7319 0.8713
2.750 0.1155 0.03532 0.02921 0.0087 0.7295 0.8727
3.000 0.1559 0.03516 0.02905 0.0062 0.7279 0.8735
3.250 0.1984 0.03499 0.02888 0.0035 0.7267 0.8741
3.500 0.1991 0.03539 0.02929 0.0060 0.7143 0.8761
3.750 0.2376 0.03508 0.02900 0.0042 0.7124 0.8769
4.000 0.2779 0.03477 0.02871 0.0021 0.7111 0.8777
4.250 0.2791 0.03520 0.02918 0.0052 0.6989 0.8797
4.500 0.3178 0.03480 0.02881 0.0035 0.6969 0.8808
4.750 0.3579 0.03435 0.02842 0.0016 0.6955 0.8822
5.000 0.3632 0.03483 0.02894 0.0040 0.6836 0.8848
5.250 0.4028 0.03432 0.02847 0.0021 0.6815 0.8861
5.500 0.4456 0.03362 0.02784 -0.0001 0.6800 0.8873
5.750 0.4906 0.03278 0.02707 -0.0026 0.6790 0.8885
6.000 0.4989 0.03319 0.02753 -0.0008 0.6662 0.8910
6.250 0.5427 0.03224 0.02667 -0.0029 0.6648 0.8922
6.500 0.5844 0.03122 0.02575 -0.0045 0.6637 0.8935
7.750 0.7489 0.02422 0.01921 -0.0043 0.6180 0.9051
8.000 0.7556 0.02460 0.01966 -0.0017 0.5972 0.9089
8.250 0.7853 0.02351 0.01863 -0.0012 0.5757 0.9117
8.500 0.8579 0.02010 0.01483 -0.0049 0.5070 0.9124
8.750 0.8620 0.02073 0.01501 -0.0015 0.4338 0.9164
9.000 0.8531 0.02225 0.01614 0.0028 0.3697 0.9215
9.250 0.8388 0.02391 0.01746 0.0079 0.3096 0.9269
9.500 0.8237 0.02595 0.01908 0.0123 0.2375 0.9331
9.750 0.8084 0.02823 0.02082 0.0165 0.1539 0.9393
10.000 0.7983 0.03051 0.02260 0.0198 0.0922 0.9460
10.250 0.8012 0.03214 0.02409 0.0217 0.0733 0.9525
10.500 0.8100 0.03353 0.02549 0.0227 0.0644 0.9601
10.750 0.8212 0.03514 0.02713 0.0230 0.0585 0.9677
11.000 0.8374 0.03664 0.02864 0.0223 0.0536 0.9762
11.250 0.8520 0.03800 0.03004 0.0220 0.0503 0.9936
11.500 0.8676 0.03928 0.03133 0.0219 0.0471 1.0000
11.750 0.8831 0.04065 0.03262 0.0219 0.0448 1.0000
12.000 0.9044 0.04168 0.03370 0.0217 0.0432 1.0000
12.250 0.9274 0.04265 0.03472 0.0213 0.0417 1.0000
12.500 0.9517 0.04361 0.03570 0.0209 0.0401 1.0000
12.750 0.9808 0.04446 0.03646 0.0201 0.0385 1.0000
13.000 1.0130 0.04550 0.03757 0.0192 0.0370 1.0000
13.250 1.0367 0.04684 0.03906 0.0187 0.0360 1.0000
13.500 1.0640 0.04828 0.04066 0.0181 0.0353 1.0000
13.750 1.0890 0.04999 0.04254 0.0175 0.0347 1.0000
14.000 1.1110 0.05196 0.04468 0.0172 0.0343 1.0000
14.250 1.1288 0.05425 0.04719 0.0171 0.0341 1.0000
14.500 1.1399 0.05696 0.05016 0.0175 0.0340 1.0000
14.750 1.1442 0.06019 0.05369 0.0183 0.0342 1.0000
15.000 1.1413 0.06387 0.05770 0.0193 0.0345 1.0000
15.250 1.1332 0.06784 0.06197 0.0204 0.0350 1.0000
15.500 1.1203 0.07208 0.06650 0.0214 0.0352 1.0000
15.750 1.1050 0.07635 0.07103 0.0220 0.0352 1.0000
16.000 1.0877 0.08129 0.07623 0.0223 0.0357 1.0000
16.250 1.0685 0.08640 0.08156 0.0221 0.0359 1.0000
16.500 1.0480 0.09191 0.08729 0.0213 0.0362 1.0000
16.750 1.0273 0.09781 0.09338 0.0199 0.0366 1.0000
17.000 1.0048 0.10426 0.10002 0.0178 0.0368 1.0000
17.250 0.9884 0.11051 0.10640 0.0154 0.0372 1.0000
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