NACA 64(2)-215 (naca642215-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64(2)-215 (naca642215-il) Reynolds number: 100,000 Max Cl/Cd: 47.56 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca642215-il-100000.txt Download as CSV file: xf-naca642215-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-215
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4834 0.10633 0.10115 -0.0261 1.0000 0.1815
-10.750 -0.7377 0.06404 0.05840 -0.0565 1.0000 0.0840
-10.500 -0.7530 0.06042 0.05467 -0.0548 1.0000 0.0825
-10.250 -0.7693 0.05659 0.05062 -0.0529 1.0000 0.0806
-10.000 -0.7829 0.05296 0.04671 -0.0505 1.0000 0.0793
-9.750 -0.7959 0.04941 0.04280 -0.0474 1.0000 0.0777
-9.500 -0.8065 0.04663 0.03966 -0.0435 1.0000 0.0767
-9.250 -0.8198 0.04446 0.03706 -0.0385 1.0000 0.0757
-9.000 -0.8241 0.04261 0.03494 -0.0344 1.0000 0.0753
-8.750 -0.8245 0.04079 0.03287 -0.0308 1.0000 0.0751
-8.500 -0.8211 0.03884 0.03070 -0.0278 1.0000 0.0753
-8.250 -0.8145 0.03693 0.02862 -0.0252 1.0000 0.0758
-8.000 -0.8055 0.03532 0.02690 -0.0231 1.0000 0.0770
-7.750 -0.7949 0.03407 0.02558 -0.0211 1.0000 0.0792
-7.500 -0.7827 0.03280 0.02415 -0.0193 0.9998 0.0813
-7.250 -0.7418 0.03094 0.02196 -0.0222 0.9939 0.0844
-7.000 -0.7027 0.02904 0.01990 -0.0246 0.9877 0.0879
-6.750 -0.6614 0.02761 0.01855 -0.0277 0.9822 0.0949
-6.500 -0.6235 0.02630 0.01716 -0.0298 0.9750 0.1012
-6.250 -0.5835 0.02507 0.01606 -0.0326 0.9693 0.1125
-6.000 -0.5522 0.02387 0.01504 -0.0340 0.9609 0.1256
-5.750 -0.5210 0.02252 0.01395 -0.0357 0.9535 0.1517
-5.500 -0.5043 0.01986 0.01233 -0.0362 0.9440 0.2701
-5.250 -0.4898 0.01932 0.01304 -0.0339 0.9336 0.5362
-5.000 -0.4494 0.02031 0.01395 -0.0350 0.9275 0.5886
-4.750 -0.4209 0.02127 0.01490 -0.0337 0.9187 0.6146
-4.500 -0.3818 0.02235 0.01591 -0.0339 0.9129 0.6402
-4.250 -0.3502 0.02359 0.01714 -0.0323 0.9057 0.6603
-4.000 -0.3173 0.02479 0.01830 -0.0308 0.8987 0.6791
-3.750 -0.2752 0.02601 0.01945 -0.0304 0.8947 0.6975
-3.500 -0.2540 0.02671 0.02010 -0.0278 0.8855 0.7103
-3.250 -0.2197 0.02685 0.02012 -0.0283 0.8799 0.7230
-3.000 -0.1951 0.02708 0.02027 -0.0272 0.8717 0.7312
-2.750 -0.1684 0.02679 0.01987 -0.0274 0.8646 0.7397
-2.500 -0.1399 0.02680 0.01979 -0.0273 0.8581 0.7456
-2.250 -0.1252 0.02639 0.01929 -0.0265 0.8492 0.7546
-2.000 -0.0886 0.02634 0.01917 -0.0274 0.8453 0.7589
-1.750 -0.0788 0.02634 0.01912 -0.0254 0.8354 0.7663
-1.500 -0.0499 0.02603 0.01873 -0.0260 0.8302 0.7727
-1.250 -0.0319 0.02616 0.01884 -0.0246 0.8223 0.7783
-1.000 -0.0118 0.02588 0.01848 -0.0245 0.8156 0.7868
-0.750 0.0214 0.02579 0.01835 -0.0250 0.8121 0.7909
-0.500 0.0295 0.02609 0.01867 -0.0229 0.8030 0.7973
-0.250 0.0550 0.02589 0.01841 -0.0233 0.7979 0.8046
0.000 0.0891 0.02577 0.01826 -0.0239 0.7948 0.8092
0.250 0.0913 0.02623 0.01874 -0.0214 0.7850 0.8172
0.500 0.1185 0.02620 0.01869 -0.0216 0.7809 0.8232
0.750 0.1517 0.02612 0.01860 -0.0222 0.7781 0.8292
1.000 0.1499 0.02678 0.01930 -0.0193 0.7680 0.8385
1.250 0.1779 0.02682 0.01936 -0.0193 0.7641 0.8448
1.500 0.2085 0.02675 0.01928 -0.0201 0.7609 0.8529
1.750 0.2050 0.02763 0.02023 -0.0165 0.7510 0.8620
2.000 0.2351 0.02757 0.02019 -0.0168 0.7472 0.8706
2.250 0.2427 0.02822 0.02089 -0.0146 0.7400 0.8810
2.500 0.2594 0.02858 0.02131 -0.0135 0.7335 0.8905
2.750 0.2924 0.02848 0.02124 -0.0141 0.7301 0.9003
3.000 0.2915 0.02950 0.02233 -0.0113 0.7213 0.9140
3.250 0.3241 0.02965 0.02256 -0.0123 0.7161 0.9240
3.500 0.3686 0.02941 0.02239 -0.0145 0.7131 0.9331
3.750 0.3802 0.03062 0.02370 -0.0145 0.7028 0.9483
4.000 0.4342 0.03034 0.02353 -0.0184 0.6986 0.9555
4.250 0.4979 0.02951 0.02281 -0.0229 0.6957 0.9601
4.500 0.5338 0.03018 0.02363 -0.0261 0.6835 0.9713
4.750 0.6089 0.02824 0.02180 -0.0309 0.6794 0.9722
5.000 0.6632 0.02732 0.02104 -0.0347 0.6656 0.9782
5.250 0.7210 0.02526 0.01907 -0.0371 0.6506 0.9838
5.500 0.7815 0.02285 0.01670 -0.0397 0.6324 0.9887
5.750 0.8311 0.02116 0.01507 -0.0420 0.6088 0.9972
6.000 0.8538 0.02029 0.01426 -0.0405 0.5889 1.0000
6.250 0.8642 0.01970 0.01370 -0.0371 0.5705 1.0000
6.500 0.8750 0.01904 0.01302 -0.0336 0.5493 1.0000
6.750 0.8729 0.01886 0.01294 -0.0286 0.5251 1.0000
7.000 0.8789 0.01848 0.01251 -0.0245 0.4853 1.0000
7.250 0.8778 0.01867 0.01222 -0.0196 0.3667 1.0000
7.500 0.8584 0.02092 0.01330 -0.0138 0.2319 1.0000
7.750 0.8450 0.02316 0.01489 -0.0091 0.1714 1.0000
8.000 0.8422 0.02500 0.01637 -0.0058 0.1423 1.0000
8.250 0.8491 0.02655 0.01773 -0.0037 0.1237 1.0000
8.500 0.8625 0.02800 0.01903 -0.0022 0.1110 1.0000
8.750 0.8824 0.02945 0.02029 -0.0015 0.1009 1.0000
9.000 0.9074 0.03078 0.02157 -0.0012 0.0927 1.0000
9.250 0.9402 0.03244 0.02321 -0.0018 0.0856 1.0000
9.500 0.9715 0.03405 0.02479 -0.0024 0.0800 1.0000
9.750 1.0160 0.03676 0.02753 -0.0049 0.0758 1.0000
10.000 1.0386 0.03857 0.02960 -0.0044 0.0725 1.0000
10.250 1.0628 0.04055 0.03169 -0.0044 0.0695 1.0000
10.500 1.0876 0.04305 0.03434 -0.0045 0.0678 1.0000
10.750 1.1134 0.04664 0.03807 -0.0051 0.0665 1.0000
11.000 1.1275 0.05038 0.04211 -0.0043 0.0658 1.0000
11.250 1.1305 0.05297 0.04507 -0.0021 0.0654 1.0000
11.500 1.1287 0.05565 0.04812 0.0003 0.0650 1.0000
11.750 1.1210 0.05840 0.05119 0.0031 0.0646 1.0000
12.000 1.1118 0.06148 0.05455 0.0056 0.0646 1.0000
12.250 1.0996 0.06487 0.05820 0.0077 0.0647 1.0000
12.500 1.0880 0.06877 0.06232 0.0091 0.0650 1.0000
12.750 1.0799 0.07334 0.06708 0.0097 0.0656 1.0000
13.000 1.0724 0.07754 0.07148 0.0102 0.0663 1.0000
13.250 1.0069 0.08223 0.07664 0.0100 0.0678 1.0000
13.500 0.9147 0.09535 0.09024 0.0033 0.0717 1.0000
13.750 0.8686 0.10689 0.10191 -0.0034 0.0745 1.0000
14.000 0.8542 0.11479 0.10985 -0.0072 0.0761 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64(2)-215 (naca642215-il)