NACA6409 9% (n6409-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA6409 9% (n6409-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.34 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6409-il-1000000-n5.txt Download as CSV file: xf-n6409-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3661 0.02071 0.01778 -0.1548 0.9288 0.0094
-9.750 -0.3453 0.01893 0.01579 -0.1552 0.9219 0.0097
-9.500 -0.3211 0.01770 0.01437 -0.1557 0.9158 0.0100
-9.250 -0.2974 0.01669 0.01318 -0.1557 0.9091 0.0104
-9.000 -0.2729 0.01577 0.01207 -0.1558 0.9013 0.0107
-8.750 -0.2483 0.01505 0.01118 -0.1556 0.8927 0.0109
-8.500 -0.2246 0.01404 0.00997 -0.1555 0.8833 0.0112
-8.250 -0.1997 0.01342 0.00922 -0.1553 0.8737 0.0116
-8.000 -0.1739 0.01296 0.00866 -0.1551 0.8658 0.0119
-7.750 -0.1481 0.01254 0.00813 -0.1549 0.8581 0.0122
-7.500 -0.1220 0.01211 0.00759 -0.1547 0.8514 0.0126
-7.250 -0.0959 0.01173 0.00710 -0.1545 0.8439 0.0130
-7.000 -0.0698 0.01134 0.00659 -0.1542 0.8364 0.0134
-6.750 -0.0435 0.01104 0.00618 -0.1540 0.8282 0.0138
-6.500 -0.0171 0.01073 0.00575 -0.1538 0.8205 0.0141
-6.250 0.0087 0.01027 0.00516 -0.1535 0.8125 0.0145
-6.000 0.0348 0.00985 0.00464 -0.1532 0.8041 0.0150
-5.750 0.0611 0.00959 0.00430 -0.1529 0.7952 0.0155
-5.500 0.0876 0.00938 0.00401 -0.1526 0.7856 0.0161
-5.250 0.1142 0.00918 0.00373 -0.1523 0.7768 0.0166
-5.000 0.1405 0.00896 0.00342 -0.1520 0.7676 0.0170
-4.750 0.1672 0.00877 0.00314 -0.1517 0.7578 0.0175
-4.500 0.1936 0.00861 0.00289 -0.1514 0.7475 0.0179
-4.250 0.2198 0.00845 0.00264 -0.1510 0.7366 0.0184
-4.000 0.2463 0.00825 0.00238 -0.1507 0.7262 0.0194
-3.500 0.2992 0.00803 0.00203 -0.1500 0.7054 0.0214
-3.250 0.3255 0.00796 0.00189 -0.1496 0.6934 0.0224
-3.000 0.3520 0.00788 0.00174 -0.1493 0.6816 0.0237
-2.750 0.3783 0.00780 0.00162 -0.1489 0.6697 0.0262
-2.500 0.4047 0.00776 0.00153 -0.1486 0.6586 0.0291
-2.250 0.4308 0.00771 0.00145 -0.1482 0.6472 0.0351
-2.000 0.4571 0.00767 0.00139 -0.1478 0.6351 0.0426
-1.750 0.4834 0.00766 0.00134 -0.1475 0.6230 0.0494
-1.500 0.5097 0.00766 0.00131 -0.1471 0.6111 0.0557
-1.250 0.5358 0.00766 0.00128 -0.1468 0.6003 0.0636
-1.000 0.5621 0.00768 0.00127 -0.1464 0.5892 0.0716
-0.750 0.5884 0.00768 0.00127 -0.1461 0.5782 0.0845
-0.500 0.6145 0.00768 0.00128 -0.1457 0.5678 0.1016
-0.250 0.6405 0.00771 0.00129 -0.1453 0.5575 0.1162
0.000 0.6669 0.00773 0.00131 -0.1451 0.5477 0.1300
0.250 0.6931 0.00775 0.00135 -0.1447 0.5390 0.1474
0.500 0.7193 0.00779 0.00138 -0.1444 0.5299 0.1640
0.750 0.7456 0.00782 0.00143 -0.1441 0.5221 0.1814
1.000 0.7715 0.00787 0.00149 -0.1437 0.5137 0.2044
1.250 0.7979 0.00789 0.00155 -0.1434 0.5067 0.2269
1.500 0.8238 0.00793 0.00162 -0.1431 0.4996 0.2561
1.750 0.8499 0.00794 0.00170 -0.1428 0.4935 0.2911
2.000 0.8760 0.00796 0.00179 -0.1425 0.4874 0.3308
2.250 0.9010 0.00786 0.00191 -0.1421 0.4816 0.4420
2.750 0.9577 0.00706 0.00222 -0.1427 0.4707 1.0000
3.000 0.9835 0.00717 0.00232 -0.1423 0.4658 1.0000
3.250 1.0096 0.00727 0.00240 -0.1419 0.4607 1.0000
3.500 1.0352 0.00739 0.00250 -0.1415 0.4556 1.0000
3.750 1.0607 0.00752 0.00262 -0.1411 0.4509 1.0000
4.000 1.0866 0.00762 0.00273 -0.1407 0.4459 1.0000
4.250 1.1119 0.00776 0.00285 -0.1403 0.4405 1.0000
4.500 1.1371 0.00789 0.00298 -0.1398 0.4352 1.0000
4.750 1.1619 0.00805 0.00311 -0.1393 0.4251 1.0000
5.000 1.1848 0.00829 0.00328 -0.1384 0.4060 1.0000
5.250 1.2059 0.00865 0.00348 -0.1372 0.3749 1.0000
5.500 1.2231 0.00923 0.00381 -0.1353 0.3254 1.0000
5.750 1.2395 0.00988 0.00421 -0.1334 0.2795 1.0000
6.000 1.2523 0.01076 0.00475 -0.1308 0.2209 1.0000
6.250 1.2662 0.01153 0.00527 -0.1284 0.1743 1.0000
6.500 1.2788 0.01233 0.00583 -0.1258 0.1291 1.0000
6.750 1.2906 0.01303 0.00635 -0.1230 0.0951 1.0000
7.000 1.3034 0.01365 0.00685 -0.1203 0.0701 1.0000
7.250 1.3174 0.01422 0.00732 -0.1179 0.0523 1.0000
7.500 1.3323 0.01473 0.00777 -0.1157 0.0407 1.0000
7.750 1.3481 0.01520 0.00822 -0.1138 0.0328 1.0000
8.000 1.3630 0.01572 0.00871 -0.1117 0.0255 1.0000
8.250 1.3780 0.01624 0.00921 -0.1096 0.0202 1.0000
8.500 1.3931 0.01676 0.00973 -0.1076 0.0169 1.0000
8.750 1.4080 0.01729 0.01026 -0.1057 0.0149 1.0000
9.000 1.4232 0.01781 0.01082 -0.1038 0.0137 1.0000
9.250 1.4380 0.01836 0.01141 -0.1019 0.0129 1.0000
9.500 1.4519 0.01897 0.01204 -0.1000 0.0122 1.0000
9.750 1.4652 0.01964 0.01274 -0.0980 0.0116 1.0000
10.000 1.4770 0.02039 0.01354 -0.0959 0.0109 1.0000
10.250 1.4891 0.02116 0.01436 -0.0938 0.0105 1.0000
10.500 1.5015 0.02193 0.01518 -0.0919 0.0103 1.0000
10.750 1.5134 0.02275 0.01605 -0.0901 0.0101 1.0000
11.000 1.5247 0.02362 0.01698 -0.0882 0.0097 1.0000
11.250 1.5353 0.02458 0.01799 -0.0863 0.0094 1.0000
11.500 1.5448 0.02564 0.01911 -0.0844 0.0092 1.0000
11.750 1.5539 0.02676 0.02030 -0.0826 0.0089 1.0000
12.000 1.5620 0.02800 0.02159 -0.0808 0.0087 1.0000
12.250 1.5692 0.02936 0.02300 -0.0790 0.0085 1.0000
12.500 1.5746 0.03091 0.02462 -0.0771 0.0082 1.0000
12.750 1.5764 0.03282 0.02662 -0.0752 0.0078 1.0000
13.000 1.5827 0.03443 0.02830 -0.0737 0.0077 1.0000
13.250 1.5885 0.03612 0.03007 -0.0723 0.0077 1.0000
13.500 1.5940 0.03790 0.03194 -0.0711 0.0075 1.0000
13.750 1.5988 0.03982 0.03394 -0.0700 0.0074 1.0000
14.000 1.6030 0.04188 0.03608 -0.0689 0.0073 1.0000
14.250 1.6070 0.04401 0.03829 -0.0680 0.0072 1.0000
14.500 1.6096 0.04637 0.04073 -0.0672 0.0070 1.0000
14.750 1.6126 0.04876 0.04320 -0.0665 0.0069 1.0000
15.000 1.6163 0.05114 0.04566 -0.0660 0.0066 1.0000
15.250 1.6183 0.05376 0.04836 -0.0655 0.0065 1.0000
15.500 1.6210 0.05637 0.05104 -0.0653 0.0063 1.0000
15.750 1.6213 0.05936 0.05413 -0.0651 0.0062 1.0000
16.000 1.6220 0.06236 0.05721 -0.0650 0.0061 1.0000
16.250 1.6214 0.06562 0.06055 -0.0651 0.0060 1.0000
16.500 1.6191 0.06916 0.06418 -0.0653 0.0059 1.0000
16.750 1.6163 0.07287 0.06798 -0.0657 0.0058 1.0000
17.000 1.6108 0.07707 0.07229 -0.0663 0.0056 1.0000
17.250 1.6033 0.08166 0.07698 -0.0671 0.0055 1.0000
17.500 1.6021 0.08535 0.08077 -0.0679 0.0055 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA6409 9% (n6409-il)