NACA6409 9% (n6409-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA6409 9% (n6409-il) Reynolds number: 500,000 Max Cl/Cd: 118.58 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6409-il-500000-n5.txt Download as CSV file: xf-n6409-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA6409 9%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1682 0.09359 0.09116 -0.0743 0.9740 0.0102
-9.250 -0.1603 0.08762 0.08519 -0.0794 0.9712 0.0108
-9.000 -0.1535 0.08337 0.08095 -0.0824 0.9644 0.0110
-8.750 -0.1337 0.08114 0.07871 -0.0858 0.9606 0.0113
-8.500 -0.1153 0.07742 0.07498 -0.0906 0.9558 0.0115
-8.250 -0.0970 0.07376 0.07129 -0.0955 0.9487 0.0119
-7.750 -0.1417 0.02118 0.01733 -0.1516 0.9047 0.0141
-7.500 -0.1187 0.01893 0.01474 -0.1526 0.8963 0.0147
-7.250 -0.0931 0.01814 0.01383 -0.1528 0.8883 0.0152
-7.000 -0.0678 0.01713 0.01262 -0.1530 0.8817 0.0157
-6.750 -0.0428 0.01604 0.01129 -0.1531 0.8746 0.0162
-6.500 -0.0171 0.01501 0.00999 -0.1531 0.8681 0.0168
-6.250 0.0084 0.01418 0.00893 -0.1530 0.8608 0.0173
-6.000 0.0351 0.01356 0.00810 -0.1529 0.8542 0.0179
-5.750 0.0606 0.01278 0.00713 -0.1527 0.8462 0.0186
-5.500 0.0870 0.01221 0.00644 -0.1525 0.8389 0.0192
-5.250 0.1134 0.01179 0.00591 -0.1523 0.8309 0.0199
-5.000 0.1401 0.01138 0.00539 -0.1521 0.8234 0.0205
-4.750 0.1666 0.01101 0.00491 -0.1518 0.8148 0.0213
-4.500 0.1932 0.01070 0.00448 -0.1516 0.8062 0.0221
-4.250 0.2199 0.01045 0.00411 -0.1513 0.7972 0.0229
-4.000 0.2462 0.01006 0.00365 -0.1510 0.7880 0.0241
-3.750 0.2728 0.00983 0.00334 -0.1507 0.7791 0.0253
-3.500 0.2992 0.00964 0.00306 -0.1503 0.7689 0.0266
-3.250 0.3258 0.00947 0.00281 -0.1500 0.7586 0.0283
-3.000 0.3521 0.00929 0.00257 -0.1496 0.7483 0.0309
-2.750 0.3784 0.00918 0.00239 -0.1492 0.7379 0.0348
-2.500 0.4048 0.00905 0.00224 -0.1488 0.7272 0.0403
-2.250 0.4310 0.00897 0.00210 -0.1484 0.7161 0.0468
-2.000 0.4570 0.00891 0.00200 -0.1480 0.7044 0.0544
-1.500 0.5090 0.00883 0.00185 -0.1472 0.6810 0.0726
-1.250 0.5350 0.00880 0.00180 -0.1467 0.6697 0.0847
-1.000 0.5607 0.00879 0.00177 -0.1463 0.6579 0.0995
-0.750 0.5863 0.00879 0.00176 -0.1458 0.6457 0.1151
-0.500 0.6119 0.00881 0.00175 -0.1453 0.6338 0.1303
-0.250 0.6377 0.00881 0.00176 -0.1449 0.6225 0.1486
0.000 0.6634 0.00884 0.00178 -0.1444 0.6115 0.1675
0.250 0.6888 0.00889 0.00181 -0.1439 0.6003 0.1873
0.500 0.7142 0.00892 0.00186 -0.1435 0.5894 0.2125
0.750 0.7399 0.00895 0.00191 -0.1430 0.5793 0.2382
1.000 0.7651 0.00899 0.00198 -0.1425 0.5694 0.2708
1.250 0.7904 0.00900 0.00206 -0.1421 0.5598 0.3132
1.500 0.8157 0.00896 0.00215 -0.1417 0.5512 0.3775
2.000 0.8714 0.00805 0.00245 -0.1420 0.5342 1.0000
2.250 0.8966 0.00820 0.00254 -0.1414 0.5267 1.0000
2.500 0.9223 0.00833 0.00263 -0.1410 0.5193 1.0000
2.750 0.9472 0.00850 0.00274 -0.1404 0.5124 1.0000
3.000 0.9730 0.00862 0.00285 -0.1400 0.5058 1.0000
3.250 0.9980 0.00878 0.00297 -0.1395 0.4994 1.0000
3.500 1.0234 0.00893 0.00310 -0.1390 0.4935 1.0000
3.750 1.0486 0.00908 0.00325 -0.1385 0.4874 1.0000
4.000 1.0732 0.00926 0.00340 -0.1379 0.4817 1.0000
4.250 1.0986 0.00939 0.00355 -0.1375 0.4760 1.0000
4.500 1.1233 0.00956 0.00372 -0.1369 0.4704 1.0000
4.750 1.1480 0.00973 0.00390 -0.1364 0.4650 1.0000
5.000 1.1728 0.00989 0.00408 -0.1358 0.4590 1.0000
5.250 1.1963 0.01011 0.00428 -0.1351 0.4520 1.0000
5.500 1.2197 0.01029 0.00449 -0.1343 0.4405 1.0000
5.750 1.2402 0.01058 0.00470 -0.1329 0.4190 1.0000
6.000 1.2585 0.01096 0.00494 -0.1312 0.3860 1.0000
6.250 1.2741 0.01150 0.00527 -0.1291 0.3448 1.0000
6.500 1.2885 0.01215 0.00570 -0.1267 0.3036 1.0000
6.750 1.3007 0.01287 0.00622 -0.1241 0.2623 1.0000
7.000 1.3090 0.01379 0.00686 -0.1207 0.2116 1.0000
7.250 1.3144 0.01489 0.00765 -0.1170 0.1572 1.0000
7.500 1.3196 0.01600 0.00849 -0.1134 0.1102 1.0000
7.750 1.3279 0.01693 0.00925 -0.1103 0.0786 1.0000
8.000 1.3381 0.01777 0.01000 -0.1076 0.0579 1.0000
8.250 1.3498 0.01852 0.01070 -0.1052 0.0447 1.0000
8.500 1.3620 0.01926 0.01142 -0.1029 0.0356 1.0000
8.750 1.3741 0.02001 0.01216 -0.1007 0.0290 1.0000
9.000 1.3855 0.02082 0.01297 -0.0984 0.0239 1.0000
9.250 1.3972 0.02163 0.01382 -0.0963 0.0206 1.0000
9.500 1.4081 0.02250 0.01472 -0.0941 0.0184 1.0000
9.750 1.4199 0.02335 0.01563 -0.0921 0.0172 1.0000
10.000 1.4303 0.02430 0.01664 -0.0901 0.0161 1.0000
10.250 1.4396 0.02537 0.01776 -0.0880 0.0152 1.0000
10.500 1.4469 0.02662 0.01907 -0.0858 0.0144 1.0000
10.750 1.4554 0.02782 0.02036 -0.0838 0.0140 1.0000
11.000 1.4636 0.02908 0.02170 -0.0820 0.0136 1.0000
11.250 1.4710 0.03045 0.02316 -0.0802 0.0132 1.0000
11.500 1.4773 0.03196 0.02475 -0.0784 0.0128 1.0000
11.750 1.4837 0.03351 0.02639 -0.0767 0.0124 1.0000
12.000 1.4891 0.03521 0.02817 -0.0752 0.0120 1.0000
12.250 1.4936 0.03704 0.03009 -0.0737 0.0116 1.0000
12.500 1.4962 0.03913 0.03226 -0.0723 0.0113 1.0000
12.750 1.4965 0.04154 0.03475 -0.0709 0.0110 1.0000
13.000 1.4944 0.04430 0.03761 -0.0696 0.0107 1.0000
13.250 1.4953 0.04685 0.04026 -0.0686 0.0106 1.0000
13.500 1.4979 0.04929 0.04281 -0.0679 0.0104 1.0000
13.750 1.4995 0.05194 0.04557 -0.0672 0.0103 1.0000
14.000 1.5005 0.05472 0.04846 -0.0667 0.0101 1.0000
14.250 1.5018 0.05754 0.05138 -0.0663 0.0099 1.0000
14.500 1.5031 0.06044 0.05439 -0.0660 0.0097 1.0000
14.750 1.5037 0.06349 0.05755 -0.0659 0.0095 1.0000
15.000 1.5043 0.06661 0.06077 -0.0659 0.0092 1.0000
15.250 1.5048 0.06980 0.06407 -0.0660 0.0090 1.0000
15.500 1.5047 0.07314 0.06750 -0.0663 0.0088 1.0000
15.750 1.5044 0.07657 0.07103 -0.0666 0.0086 1.0000
16.000 1.5033 0.08018 0.07474 -0.0671 0.0085 1.0000
16.250 1.5016 0.08392 0.07858 -0.0677 0.0084 1.0000
16.500 1.4992 0.08784 0.08260 -0.0685 0.0082 1.0000
16.750 1.4961 0.09190 0.08676 -0.0693 0.0081 1.0000
17.000 1.4915 0.09624 0.09118 -0.0703 0.0079 1.0000
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Polar data table (+)
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