NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 100,000 Max Cl/Cd: 32.73 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662415-il-100000-n5.txt Download as CSV file: xf-naca662415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4008 0.13983 0.13465 -0.0538 1.0000 0.0625
-13.250 -0.4045 0.13722 0.13208 -0.0539 0.9987 0.0643
-13.000 -0.4159 0.13100 0.12592 -0.0625 0.9927 0.0681
-12.500 -0.4180 0.11069 0.10553 -0.0718 0.9862 0.0385
-12.250 -0.4121 0.10595 0.10077 -0.0748 0.9825 0.0381
-12.000 -0.4095 0.10043 0.09525 -0.0787 0.9786 0.0377
-11.750 -0.4105 0.09335 0.08816 -0.0842 0.9754 0.0373
-11.500 -0.4218 0.08380 0.07857 -0.0922 0.9707 0.0369
-11.250 -0.4404 0.07519 0.06984 -0.0998 0.9655 0.0366
-11.000 -0.4579 0.06849 0.06295 -0.1052 0.9605 0.0362
-10.750 -0.4762 0.06350 0.05773 -0.1075 0.9528 0.0363
-10.500 -0.4909 0.05923 0.05320 -0.1086 0.9461 0.0363
-10.250 -0.5071 0.05616 0.04987 -0.1069 0.9373 0.0366
-10.000 -0.5193 0.05350 0.04693 -0.1044 0.9299 0.0368
-9.750 -0.5273 0.05098 0.04411 -0.1017 0.9227 0.0370
-9.500 -0.5261 0.04800 0.04074 -0.1002 0.9185 0.0371
-9.250 -0.5311 0.04606 0.03852 -0.0964 0.9110 0.0372
-9.000 -0.5265 0.04369 0.03577 -0.0942 0.9060 0.0374
-8.750 -0.5150 0.04123 0.03288 -0.0929 0.9028 0.0378
-8.500 -0.5113 0.03968 0.03095 -0.0896 0.8974 0.0382
-8.250 -0.5031 0.03817 0.02910 -0.0870 0.8926 0.0390
-8.000 -0.4842 0.03643 0.02725 -0.0866 0.8899 0.0401
-7.750 -0.4619 0.03500 0.02565 -0.0864 0.8877 0.0412
-7.500 -0.4365 0.03344 0.02387 -0.0865 0.8861 0.0422
-7.250 -0.4267 0.03261 0.02286 -0.0836 0.8808 0.0427
-7.000 -0.4072 0.03152 0.02160 -0.0824 0.8773 0.0437
-6.750 -0.3829 0.03050 0.02040 -0.0821 0.8748 0.0453
-6.500 -0.3566 0.02962 0.01929 -0.0820 0.8729 0.0471
-6.250 -0.3282 0.02845 0.01813 -0.0824 0.8715 0.0488
-6.000 -0.3007 0.02755 0.01723 -0.0827 0.8702 0.0503
-5.750 -0.2945 0.02733 0.01701 -0.0792 0.8655 0.0514
-5.500 -0.2828 0.02700 0.01665 -0.0766 0.8616 0.0531
-5.250 -0.2644 0.02656 0.01614 -0.0753 0.8588 0.0559
-5.000 -0.2443 0.02597 0.01552 -0.0743 0.8565 0.0587
-4.750 -0.2227 0.02541 0.01494 -0.0736 0.8547 0.0615
-4.500 -0.2128 0.02527 0.01475 -0.0707 0.8513 0.0642
-4.250 -0.2122 0.02540 0.01482 -0.0662 0.8463 0.0671
-4.000 -0.1978 0.02514 0.01458 -0.0642 0.8434 0.0729
-3.750 -0.1773 0.02483 0.01424 -0.0632 0.8413 0.0823
-3.500 -0.1557 0.02428 0.01384 -0.0625 0.8395 0.1076
-3.250 -0.1463 0.02261 0.01335 -0.0604 0.8377 0.3322
-3.000 -0.1701 0.02246 0.01387 -0.0520 0.8305 0.4608
-2.750 -0.1664 0.02300 0.01538 -0.0454 0.8273 0.6896
-2.500 -0.1490 0.02378 0.01613 -0.0422 0.8250 0.7464
-2.250 -0.1314 0.02476 0.01706 -0.0384 0.8232 0.7833
-2.000 -0.1099 0.02588 0.01815 -0.0346 0.8221 0.8078
-1.750 -0.1202 0.02654 0.01881 -0.0276 0.8156 0.8214
-1.500 -0.1073 0.02712 0.01933 -0.0239 0.8124 0.8371
-1.250 -0.0872 0.02731 0.01941 -0.0224 0.8099 0.8475
-1.000 -0.0601 0.02733 0.01932 -0.0225 0.8080 0.8516
-0.750 -0.0304 0.02733 0.01922 -0.0231 0.8066 0.8546
-0.500 -0.0285 0.02760 0.01944 -0.0192 0.8010 0.8604
-0.250 -0.0146 0.02766 0.01942 -0.0175 0.7968 0.8652
0.000 0.0108 0.02770 0.01940 -0.0175 0.7942 0.8675
0.250 0.0394 0.02770 0.01933 -0.0181 0.7922 0.8695
0.500 0.0703 0.02767 0.01924 -0.0190 0.7906 0.8718
0.750 0.0727 0.02801 0.01957 -0.0155 0.7838 0.8765
1.000 0.0948 0.02808 0.01959 -0.0153 0.7799 0.8794
1.250 0.1231 0.02808 0.01956 -0.0159 0.7773 0.8815
1.500 0.1547 0.02806 0.01953 -0.0168 0.7753 0.8834
2.000 0.1868 0.02852 0.01999 -0.0141 0.7642 0.8900
2.250 0.2164 0.02852 0.02000 -0.0148 0.7614 0.8924
2.500 0.2497 0.02846 0.01994 -0.0162 0.7593 0.8946
2.750 0.2578 0.02888 0.02040 -0.0137 0.7511 0.8984
3.000 0.2844 0.02895 0.02051 -0.0139 0.7471 0.9011
3.250 0.3170 0.02886 0.02047 -0.0149 0.7445 0.9037
3.500 0.3520 0.02873 0.02039 -0.0163 0.7427 0.9062
3.750 0.3562 0.02925 0.02096 -0.0134 0.7319 0.9117
4.000 0.3898 0.02910 0.02088 -0.0145 0.7291 0.9138
4.500 0.4336 0.02928 0.02124 -0.0133 0.7155 0.9214
4.750 0.4702 0.02892 0.02098 -0.0147 0.7126 0.9242
5.000 0.4817 0.02927 0.02143 -0.0127 0.7015 0.9297
5.250 0.5175 0.02885 0.02115 -0.0138 0.6980 0.9330
5.500 0.5317 0.02911 0.02152 -0.0123 0.6868 0.9397
5.750 0.5702 0.02844 0.02101 -0.0136 0.6826 0.9427
6.000 0.5898 0.02842 0.02114 -0.0126 0.6699 0.9487
6.250 0.6174 0.02769 0.02057 -0.0122 0.6557 0.9541
6.500 0.6502 0.02626 0.01926 -0.0118 0.6360 0.9591
6.750 0.6620 0.02643 0.01956 -0.0102 0.5962 0.9682
7.000 0.7286 0.02226 0.01488 -0.0109 0.4883 0.9677
7.500 0.7514 0.02425 0.01543 -0.0076 0.2517 0.9976
7.750 0.7525 0.02592 0.01640 -0.0051 0.1470 1.0000
8.000 0.7605 0.02741 0.01741 -0.0035 0.0875 1.0000
8.250 0.7736 0.02861 0.01844 -0.0025 0.0702 1.0000
8.500 0.7885 0.02969 0.01954 -0.0017 0.0623 1.0000
8.750 0.8028 0.03082 0.02071 -0.0009 0.0566 1.0000
9.000 0.8174 0.03195 0.02188 -0.0002 0.0525 1.0000
9.250 0.8296 0.03328 0.02321 0.0008 0.0498 1.0000
9.500 0.8445 0.03444 0.02448 0.0015 0.0471 1.0000
9.750 0.8593 0.03565 0.02575 0.0022 0.0444 1.0000
10.000 0.8735 0.03698 0.02706 0.0029 0.0423 1.0000
10.250 0.8912 0.03827 0.02838 0.0035 0.0407 1.0000
10.500 0.9122 0.03943 0.02965 0.0038 0.0390 1.0000
10.750 0.9334 0.04064 0.03095 0.0040 0.0371 1.0000
11.000 0.9548 0.04193 0.03226 0.0041 0.0355 1.0000
11.250 0.9831 0.04348 0.03373 0.0036 0.0339 1.0000
11.500 1.0086 0.04504 0.03552 0.0035 0.0331 1.0000
11.750 1.0330 0.04686 0.03760 0.0035 0.0323 1.0000
12.000 1.0537 0.04896 0.03996 0.0037 0.0315 1.0000
12.250 1.0684 0.05115 0.04241 0.0043 0.0307 1.0000
12.500 1.0792 0.05346 0.04496 0.0051 0.0300 1.0000
12.750 1.0871 0.05563 0.04731 0.0060 0.0292 1.0000
13.000 1.0928 0.05796 0.04980 0.0069 0.0285 1.0000
13.250 1.0969 0.06058 0.05261 0.0078 0.0281 1.0000
13.500 1.0986 0.06348 0.05571 0.0087 0.0277 1.0000
13.750 1.0966 0.06672 0.05917 0.0096 0.0275 1.0000
14.000 1.0906 0.07030 0.06299 0.0105 0.0274 1.0000
14.250 1.0797 0.07416 0.06709 0.0113 0.0273 1.0000
14.500 1.0647 0.07834 0.07155 0.0119 0.0272 1.0000
14.750 1.0485 0.08280 0.07628 0.0119 0.0272 1.0000
15.000 1.0295 0.08779 0.08152 0.0114 0.0272 1.0000
15.250 1.0105 0.09314 0.08709 0.0102 0.0273 1.0000
15.500 0.9906 0.09903 0.09320 0.0082 0.0273 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(2)-415 (naca662415-il)