NACA6409 9% (n6409-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA6409 9% (n6409-il) Reynolds number: 500,000 Max Cl/Cd: 122.39 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6409-il-500000.txt Download as CSV file: xf-n6409-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2522 0.11576 0.11348 -0.0491 0.9935 0.0189
-10.000 -0.2425 0.11172 0.10945 -0.0543 0.9908 0.0191
-9.750 -0.2293 0.10767 0.10539 -0.0587 0.9885 0.0191
-9.500 -0.2163 0.10266 0.10039 -0.0619 0.9868 0.0193
-9.250 -0.1967 0.09925 0.09697 -0.0638 0.9855 0.0197
-9.000 -0.1764 0.09606 0.09377 -0.0671 0.9843 0.0204
-8.750 -0.1622 0.09278 0.09049 -0.0701 0.9800 0.0209
-8.500 -0.1446 0.08914 0.08684 -0.0743 0.9765 0.0217
-8.250 -0.0373 0.06404 0.06183 -0.0927 0.9634 0.0247
-8.000 -0.0154 0.06166 0.05944 -0.0939 0.9617 0.0259
-7.750 0.0009 0.05786 0.05564 -0.0976 0.9595 0.0269
-7.500 0.0128 0.05404 0.05181 -0.1011 0.9548 0.0282
-7.250 0.0165 0.04931 0.04707 -0.1085 0.9450 0.0302
-7.000 0.0248 0.04531 0.04306 -0.1130 0.9354 0.0303
-6.750 0.0308 0.03888 0.03659 -0.1185 0.9281 0.0309
-6.500 0.0419 0.03708 0.03478 -0.1177 0.9194 0.0316
-6.250 0.0578 0.03452 0.03218 -0.1196 0.9126 0.0324
-6.000 0.0714 0.03193 0.02955 -0.1216 0.9034 0.0338
-5.750 0.0880 0.02806 0.02560 -0.1264 0.8949 0.0357
-5.500 0.1019 0.01927 0.01518 -0.1556 0.9026 0.0265
-5.250 0.1256 0.01639 0.01177 -0.1558 0.8962 0.0269
-5.000 0.1507 0.01493 0.01000 -0.1556 0.8893 0.0277
-4.750 0.1785 0.01396 0.00877 -0.1557 0.8835 0.0290
-4.500 0.2040 0.01326 0.00787 -0.1551 0.8758 0.0300
-4.250 0.2320 0.01218 0.00652 -0.1552 0.8700 0.0308
-4.000 0.2563 0.01121 0.00544 -0.1545 0.8618 0.0322
-3.750 0.2846 0.01077 0.00490 -0.1545 0.8553 0.0338
-3.500 0.3103 0.01045 0.00452 -0.1540 0.8465 0.0359
-3.250 0.3380 0.01019 0.00415 -0.1538 0.8389 0.0379
-3.000 0.3637 0.00958 0.00348 -0.1533 0.8302 0.0413
-2.750 0.3907 0.00936 0.00321 -0.1530 0.8218 0.0455
-2.500 0.4175 0.00905 0.00286 -0.1527 0.8130 0.0524
-2.250 0.4438 0.00887 0.00264 -0.1522 0.8031 0.0620
-2.000 0.4706 0.00875 0.00248 -0.1519 0.7937 0.0726
-1.750 0.4972 0.00863 0.00233 -0.1515 0.7837 0.0851
-1.500 0.5234 0.00852 0.00223 -0.1511 0.7732 0.0992
-1.250 0.5497 0.00844 0.00213 -0.1507 0.7626 0.1155
-1.000 0.5758 0.00836 0.00206 -0.1503 0.7515 0.1362
-0.750 0.6017 0.00831 0.00202 -0.1498 0.7397 0.1589
-0.500 0.6275 0.00826 0.00200 -0.1494 0.7279 0.1842
-0.250 0.6533 0.00823 0.00199 -0.1489 0.7159 0.2125
0.000 0.6788 0.00822 0.00200 -0.1484 0.7034 0.2459
0.250 0.7041 0.00821 0.00201 -0.1478 0.6909 0.2839
0.500 0.7291 0.00816 0.00205 -0.1473 0.6783 0.3392
0.750 0.7444 0.00715 0.00224 -0.1449 0.6658 0.8025
1.250 0.8106 0.00717 0.00228 -0.1470 0.6399 1.0000
1.500 0.8356 0.00732 0.00234 -0.1464 0.6276 1.0000
1.750 0.8605 0.00748 0.00240 -0.1458 0.6160 1.0000
2.000 0.8854 0.00765 0.00248 -0.1451 0.6048 1.0000
2.250 0.9106 0.00780 0.00257 -0.1446 0.5939 1.0000
2.500 0.9357 0.00796 0.00267 -0.1440 0.5842 1.0000
2.750 0.9606 0.00815 0.00278 -0.1434 0.5748 1.0000
3.000 0.9860 0.00829 0.00291 -0.1430 0.5659 1.0000
3.250 1.0109 0.00849 0.00304 -0.1424 0.5580 1.0000
3.500 1.0363 0.00863 0.00318 -0.1419 0.5498 1.0000
3.750 1.0613 0.00884 0.00333 -0.1414 0.5427 1.0000
4.000 1.0866 0.00898 0.00349 -0.1409 0.5352 1.0000
4.250 1.1114 0.00920 0.00366 -0.1404 0.5287 1.0000
4.500 1.1367 0.00934 0.00384 -0.1399 0.5218 1.0000
4.750 1.1614 0.00955 0.00403 -0.1394 0.5153 1.0000
5.000 1.1864 0.00971 0.00422 -0.1389 0.5087 1.0000
5.250 1.2105 0.00992 0.00441 -0.1382 0.5010 1.0000
5.500 1.2337 0.01008 0.00460 -0.1373 0.4905 1.0000
5.750 1.2548 0.01028 0.00478 -0.1360 0.4749 1.0000
6.000 1.2748 0.01052 0.00496 -0.1345 0.4566 1.0000
6.250 1.2957 0.01076 0.00517 -0.1332 0.4409 1.0000
6.500 1.3174 0.01098 0.00540 -0.1321 0.4275 1.0000
6.750 1.3383 0.01123 0.00565 -0.1309 0.4123 1.0000
7.000 1.3575 0.01153 0.00593 -0.1293 0.3925 1.0000
7.250 1.3744 0.01194 0.00624 -0.1273 0.3655 1.0000
7.500 1.3864 0.01250 0.00665 -0.1245 0.3269 1.0000
7.750 1.3920 0.01342 0.00727 -0.1206 0.2753 1.0000
8.000 1.3922 0.01472 0.00819 -0.1160 0.2089 1.0000
8.250 1.3886 0.01630 0.00934 -0.1111 0.1395 1.0000
8.500 1.3855 0.01789 0.01058 -0.1064 0.0841 1.0000
8.750 1.3865 0.01927 0.01174 -0.1024 0.0518 1.0000
9.000 1.3918 0.02044 0.01285 -0.0992 0.0370 1.0000
9.250 1.3987 0.02154 0.01396 -0.0963 0.0305 1.0000
9.500 1.4075 0.02256 0.01502 -0.0938 0.0273 1.0000
9.750 1.4099 0.02403 0.01655 -0.0906 0.0247 1.0000
10.000 1.4198 0.02505 0.01766 -0.0885 0.0236 1.0000
10.250 1.4275 0.02626 0.01895 -0.0862 0.0224 1.0000
10.500 1.4343 0.02757 0.02033 -0.0840 0.0215 1.0000
10.750 1.4390 0.02909 0.02191 -0.0818 0.0204 1.0000
11.000 1.4376 0.03117 0.02407 -0.0791 0.0196 1.0000
11.250 1.4348 0.03348 0.02650 -0.0766 0.0188 1.0000
11.500 1.4400 0.03521 0.02833 -0.0749 0.0185 1.0000
11.750 1.4431 0.03720 0.03041 -0.0733 0.0181 1.0000
12.000 1.4468 0.03920 0.03251 -0.0718 0.0176 1.0000
12.250 1.4492 0.04140 0.03481 -0.0704 0.0172 1.0000
12.500 1.4515 0.04369 0.03719 -0.0691 0.0168 1.0000
12.750 1.4539 0.04604 0.03962 -0.0680 0.0164 1.0000
13.000 1.4568 0.04841 0.04206 -0.0670 0.0160 1.0000
13.250 1.4590 0.05092 0.04466 -0.0661 0.0156 1.0000
13.500 1.4599 0.05362 0.04741 -0.0653 0.0152 1.0000
13.750 1.4581 0.05667 0.05055 -0.0641 0.0147 1.0000
14.000 1.4613 0.05926 0.05324 -0.0631 0.0143 1.0000
14.250 1.4665 0.06166 0.05577 -0.0626 0.0141 1.0000
14.500 1.4713 0.06415 0.05838 -0.0621 0.0138 1.0000
14.750 1.4755 0.06677 0.06112 -0.0617 0.0135 1.0000
15.000 1.4796 0.06945 0.06393 -0.0613 0.0133 1.0000
15.250 1.4828 0.07230 0.06691 -0.0611 0.0130 1.0000
15.500 1.4851 0.07530 0.07004 -0.0610 0.0127 1.0000
15.750 1.4868 0.07841 0.07326 -0.0612 0.0124 1.0000
16.000 1.4872 0.08176 0.07673 -0.0616 0.0121 1.0000
16.250 1.4872 0.08522 0.08029 -0.0621 0.0118 1.0000
16.500 1.4868 0.08874 0.08390 -0.0628 0.0116 1.0000
16.750 1.4862 0.09234 0.08758 -0.0633 0.0113 1.0000
17.000 1.4823 0.09665 0.09204 -0.0637 0.0110 1.0000
17.250 1.4697 0.10267 0.09832 -0.0647 0.0108 1.0000
17.500 1.4604 0.10796 0.10381 -0.0667 0.0108 1.0000
17.750 1.4502 0.11357 0.10961 -0.0691 0.0107 1.0000
18.000 1.4390 0.11956 0.11579 -0.0719 0.0107 1.0000
18.250 1.4269 0.12585 0.12227 -0.0749 0.0106 1.0000
18.500 1.4139 0.13253 0.12915 -0.0784 0.0106 1.0000
18.750 1.3994 0.13970 0.13651 -0.0824 0.0105 1.0000
19.000 1.3842 0.14726 0.14425 -0.0869 0.0105 1.0000
19.250 1.3678 0.15537 0.15254 -0.0919 0.0105 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA6409 9% (n6409-il)