NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 50,000 Max Cl/Cd: 28.73 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65410-il-50000.txt Download as CSV file: xf-naca65410-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4158 0.10466 0.09768 -0.0249 1.0000 0.2809
-8.750 -0.4165 0.10215 0.09524 -0.0242 1.0000 0.2968
-8.500 -0.4229 0.10015 0.09335 -0.0234 1.0000 0.3128
-8.250 -0.4027 0.09605 0.08924 -0.0212 1.0000 0.3381
-8.000 -0.3948 0.09314 0.08638 -0.0191 1.0000 0.3636
-7.750 -0.4118 0.09248 0.08588 -0.0169 1.0000 0.3855
-7.500 -0.3796 0.08781 0.08113 -0.0145 1.0000 0.4207
-7.250 -0.3711 0.08512 0.07849 -0.0122 1.0000 0.4495
-7.000 -0.3615 0.08247 0.07589 -0.0098 1.0000 0.4791
-6.750 -0.3521 0.07985 0.07332 -0.0075 1.0000 0.5089
-6.500 -0.3428 0.07720 0.07072 -0.0053 1.0000 0.5359
-5.000 -0.4950 0.04958 0.04266 -0.0361 1.0000 0.2149
-4.750 -0.4581 0.04370 0.03541 -0.0407 1.0000 0.1559
-4.500 -0.4320 0.04027 0.03133 -0.0409 1.0000 0.1395
-4.250 -0.4081 0.03709 0.02780 -0.0408 1.0000 0.1322
-4.000 -0.3801 0.03515 0.02492 -0.0406 1.0000 0.1264
-3.750 -0.3567 0.03265 0.02231 -0.0403 1.0000 0.1295
-3.500 -0.3314 0.03087 0.02018 -0.0398 1.0000 0.1302
-3.250 -0.3066 0.02931 0.01834 -0.0389 1.0000 0.1310
-3.000 -0.2834 0.02805 0.01691 -0.0377 1.0000 0.1343
-2.750 -0.2615 0.02699 0.01574 -0.0363 1.0000 0.1436
-2.500 -0.2409 0.02612 0.01478 -0.0346 1.0000 0.1531
-2.250 -0.2194 0.02519 0.01386 -0.0333 1.0000 0.1653
-2.000 -0.1958 0.02418 0.01298 -0.0330 1.0000 0.1949
-1.750 -0.1813 0.02120 0.01291 -0.0299 1.0000 0.6889
-1.500 -0.1743 0.02124 0.01322 -0.0178 1.0000 1.0000
-1.250 -0.1634 0.02113 0.01271 -0.0164 1.0000 1.0000
-1.000 -0.1465 0.02117 0.01235 -0.0162 1.0000 1.0000
-0.750 -0.1262 0.02132 0.01217 -0.0165 1.0000 1.0000
-0.500 -0.1044 0.02156 0.01211 -0.0170 1.0000 1.0000
-0.250 -0.0817 0.02187 0.01215 -0.0177 1.0000 1.0000
0.000 -0.0589 0.02224 0.01226 -0.0183 1.0000 1.0000
0.250 -0.0361 0.02265 0.01246 -0.0189 1.0000 1.0000
0.500 -0.0134 0.02310 0.01273 -0.0194 1.0000 1.0000
0.750 0.0091 0.02359 0.01306 -0.0199 1.0000 1.0000
1.000 0.0313 0.02412 0.01345 -0.0204 1.0000 1.0000
1.250 0.0532 0.02469 0.01389 -0.0209 1.0000 1.0000
1.500 0.0748 0.02529 0.01440 -0.0212 1.0000 1.0000
1.750 0.0962 0.02593 0.01496 -0.0216 1.0000 1.0000
2.000 0.1173 0.02661 0.01558 -0.0220 1.0000 1.0000
2.250 0.1380 0.02733 0.01625 -0.0223 1.0000 1.0000
2.500 0.1585 0.02808 0.01698 -0.0227 1.0000 1.0000
2.750 0.1787 0.02888 0.01776 -0.0230 1.0000 1.0000
3.000 0.1985 0.02972 0.01861 -0.0233 1.0000 1.0000
3.250 0.2180 0.03061 0.01953 -0.0237 1.0000 1.0000
3.500 0.2541 0.03208 0.02108 -0.0273 0.9908 1.0000
3.750 0.2946 0.03371 0.02280 -0.0316 0.9776 1.0000
4.000 0.3330 0.03525 0.02450 -0.0355 0.9639 1.0000
4.250 0.3705 0.03674 0.02615 -0.0390 0.9489 1.0000
4.500 0.4077 0.03821 0.02779 -0.0424 0.9329 1.0000
4.750 0.4471 0.03969 0.02949 -0.0459 0.9156 1.0000
5.000 0.4858 0.04109 0.03118 -0.0491 0.8965 1.0000
5.250 0.5205 0.04228 0.03264 -0.0514 0.8751 1.0000
5.500 0.5620 0.04340 0.03410 -0.0542 0.8507 1.0000
5.750 0.6082 0.04411 0.03529 -0.0568 0.8216 1.0000
6.000 0.7806 0.02717 0.01621 -0.0394 0.1870 1.0000
6.250 0.7964 0.02936 0.01810 -0.0373 0.1575 1.0000
6.500 0.8340 0.03158 0.02005 -0.0379 0.1330 1.0000
6.750 0.8960 0.03462 0.02298 -0.0413 0.1199 1.0000
7.000 0.9312 0.03699 0.02580 -0.0415 0.1124 1.0000
7.250 0.9667 0.04043 0.02927 -0.0424 0.1071 1.0000
7.500 0.9967 0.04423 0.03338 -0.0423 0.1065 1.0000
7.750 1.0184 0.04716 0.03698 -0.0407 0.1078 1.0000
8.000 1.0326 0.05054 0.04112 -0.0384 0.1100 1.0000
8.250 1.0441 0.05437 0.04551 -0.0364 0.1112 1.0000
8.500 1.0503 0.05845 0.05019 -0.0342 0.1132 1.0000
8.750 1.0550 0.06297 0.05514 -0.0323 0.1163 1.0000
9.000 1.0580 0.06762 0.06024 -0.0305 0.1228 1.0000
9.250 1.0464 0.07298 0.06606 -0.0285 0.1307 1.0000
9.500 1.0568 0.08075 0.07406 -0.0287 0.1474 1.0000
9.750 1.0290 0.08648 0.08019 -0.0277 0.1611 1.0000
10.000 0.9838 0.08983 0.08365 -0.0260 0.1601 1.0000
10.250 0.9329 0.09583 0.08973 -0.0288 0.1642 1.0000
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Polar data table (+)
Polar graphs
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