NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 100,000 Max Cl/Cd: 52.87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65410-il-100000.txt Download as CSV file: xf-naca65410-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4325 0.09438 0.08948 -0.0411 1.0000 0.0951
-8.750 -0.4521 0.09135 0.08659 -0.0450 1.0000 0.0970
-8.500 -0.4757 0.08831 0.08369 -0.0476 1.0000 0.0974
-8.250 -0.4500 0.08435 0.07971 -0.0427 1.0000 0.1023
-8.000 -0.4565 0.08178 0.07720 -0.0417 1.0000 0.1056
-7.750 -0.4750 0.07907 0.07465 -0.0417 1.0000 0.1069
-7.500 -0.4956 0.07619 0.07182 -0.0421 1.0000 0.1089
-7.250 -0.5228 0.07395 0.06954 -0.0424 1.0000 0.1110
-7.000 -0.5532 0.07331 0.06852 -0.0427 1.0000 0.1122
-6.750 -0.5299 0.06794 0.06362 -0.0380 1.0000 0.1173
-6.500 -0.5370 0.06553 0.06112 -0.0373 1.0000 0.1236
-6.250 -0.5423 0.06209 0.05760 -0.0369 1.0000 0.1293
-6.000 -0.5451 0.06010 0.05523 -0.0375 1.0000 0.1414
-5.750 -0.5358 0.05667 0.05208 -0.0345 1.0000 0.1465
-5.500 -0.5308 0.05403 0.04937 -0.0338 1.0000 0.1611
-5.250 -0.5251 0.05159 0.04672 -0.0340 1.0000 0.1855
-5.000 -0.5164 0.04923 0.04450 -0.0317 1.0000 0.2043
-4.750 -0.5077 0.04695 0.04223 -0.0304 1.0000 0.2325
-4.500 -0.4979 0.04499 0.04030 -0.0286 1.0000 0.2655
-4.000 -0.3799 0.03101 0.02297 -0.0394 0.9977 0.0812
-3.750 -0.3410 0.02860 0.02009 -0.0416 0.9942 0.0803
-3.500 -0.3040 0.02641 0.01749 -0.0431 0.9900 0.0771
-3.250 -0.2660 0.02479 0.01555 -0.0447 0.9859 0.0766
-3.000 -0.2289 0.02384 0.01439 -0.0464 0.9817 0.0817
-2.750 -0.1963 0.02275 0.01318 -0.0473 0.9767 0.0850
-2.500 -0.1613 0.02170 0.01228 -0.0490 0.9724 0.0911
-2.250 -0.1268 0.02102 0.01166 -0.0507 0.9678 0.1050
-2.000 -0.0948 0.02039 0.01103 -0.0520 0.9620 0.1263
-1.750 -0.0817 0.01809 0.01165 -0.0479 0.9582 0.7664
-1.500 -0.0823 0.01859 0.01225 -0.0397 0.9503 0.8555
-1.250 -0.0756 0.01889 0.01252 -0.0333 0.9433 0.9160
-1.000 0.0472 0.01945 0.01269 -0.0490 0.9489 1.0000
-0.750 0.0783 0.01954 0.01263 -0.0513 0.9427 1.0000
-0.500 0.0882 0.01955 0.01255 -0.0497 0.9329 1.0000
-0.250 0.1221 0.01972 0.01260 -0.0522 0.9276 1.0000
0.000 0.1283 0.01980 0.01260 -0.0499 0.9177 1.0000
0.250 0.1672 0.02006 0.01274 -0.0530 0.9132 1.0000
0.500 0.1834 0.02031 0.01292 -0.0523 0.9046 1.0000
0.750 0.2221 0.02061 0.01315 -0.0552 0.9000 1.0000
1.000 0.2450 0.02098 0.01346 -0.0556 0.8926 1.0000
1.250 0.2803 0.02131 0.01376 -0.0578 0.8871 1.0000
1.500 0.3107 0.02172 0.01414 -0.0592 0.8812 1.0000
1.750 0.3391 0.02211 0.01453 -0.0602 0.8743 1.0000
2.000 0.3817 0.02240 0.01485 -0.0633 0.8703 1.0000
2.250 0.3989 0.02295 0.01540 -0.0625 0.8611 1.0000
2.500 0.4410 0.02319 0.01570 -0.0654 0.8566 1.0000
2.750 0.4605 0.02372 0.01630 -0.0647 0.8470 1.0000
3.000 0.5058 0.02381 0.01651 -0.0679 0.8421 1.0000
3.250 0.5253 0.02435 0.01711 -0.0671 0.8317 1.0000
3.500 0.5760 0.02421 0.01717 -0.0708 0.8273 1.0000
3.750 0.5963 0.02467 0.01775 -0.0699 0.8158 1.0000
4.000 0.6260 0.02487 0.01811 -0.0703 0.8053 1.0000
4.250 0.7334 0.01847 0.01209 -0.0734 0.7656 1.0000
4.500 0.7730 0.01617 0.00986 -0.0710 0.7260 1.0000
4.750 0.7952 0.01504 0.00875 -0.0671 0.6645 1.0000
5.000 0.7889 0.01596 0.00789 -0.0583 0.3266 1.0000
5.250 0.7812 0.01933 0.00961 -0.0534 0.1183 1.0000
5.500 0.7951 0.02079 0.01096 -0.0512 0.0955 1.0000
5.750 0.8111 0.02216 0.01233 -0.0492 0.0856 1.0000
6.000 0.8297 0.02376 0.01381 -0.0479 0.0776 1.0000
6.250 0.8548 0.02520 0.01525 -0.0473 0.0712 1.0000
6.500 0.8882 0.02773 0.01761 -0.0481 0.0673 1.0000
6.750 0.9222 0.03008 0.02014 -0.0486 0.0656 1.0000
7.000 0.9503 0.03192 0.02230 -0.0482 0.0627 1.0000
7.250 0.9781 0.03439 0.02511 -0.0478 0.0614 1.0000
7.500 1.0042 0.03754 0.02866 -0.0471 0.0623 1.0000
7.750 1.0272 0.04128 0.03279 -0.0461 0.0643 1.0000
8.000 1.0521 0.04627 0.03800 -0.0458 0.0673 1.0000
8.250 1.0649 0.05342 0.04700 -0.0396 0.1107 1.0000
10.750 0.9840 0.10665 0.10241 -0.0301 0.1474 1.0000
11.000 0.9353 0.11247 0.10825 -0.0354 0.1480 1.0000
11.250 0.8915 0.12227 0.11796 -0.0449 0.1467 1.0000
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Polar data table (+)
Polar graphs
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