NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 200,000 Max Cl/Cd: 57.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652215-il-200000.txt Download as CSV file: xf-naca652215-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4007 0.09597 0.09261 -0.0468 1.0000 0.0843
-11.500 -0.4188 0.08889 0.08556 -0.0507 1.0000 0.0877
-9.500 -0.7657 0.04583 0.04031 -0.0513 0.9808 0.0530
-9.250 -0.7560 0.03837 0.03179 -0.0510 0.9733 0.0450
-9.000 -0.7253 0.03456 0.02765 -0.0534 0.9703 0.0454
-8.750 -0.6969 0.03182 0.02466 -0.0546 0.9640 0.0458
-8.500 -0.6621 0.02937 0.02194 -0.0566 0.9602 0.0458
-8.250 -0.6239 0.02715 0.01954 -0.0590 0.9575 0.0464
-8.000 -0.5926 0.02560 0.01790 -0.0600 0.9509 0.0474
-7.750 -0.5585 0.02440 0.01663 -0.0617 0.9456 0.0497
-7.500 -0.5248 0.02321 0.01534 -0.0629 0.9405 0.0515
-7.250 -0.4967 0.02222 0.01424 -0.0630 0.9328 0.0529
-7.000 -0.4660 0.02126 0.01320 -0.0636 0.9276 0.0543
-6.750 -0.4462 0.02003 0.01205 -0.0625 0.9186 0.0568
-6.500 -0.4250 0.01935 0.01136 -0.0616 0.9118 0.0603
-6.250 -0.4084 0.01885 0.01081 -0.0599 0.9022 0.0635
-6.000 -0.3923 0.01809 0.01002 -0.0580 0.8956 0.0670
-5.750 -0.3784 0.01748 0.00943 -0.0560 0.8867 0.0721
-5.500 -0.3617 0.01685 0.00877 -0.0543 0.8808 0.0811
-5.250 -0.3478 0.01616 0.00817 -0.0523 0.8723 0.1008
-5.000 -0.3499 0.01406 0.00713 -0.0485 0.8653 0.2911
-4.750 -0.3481 0.01287 0.00716 -0.0444 0.8571 0.5471
-4.500 -0.3247 0.01304 0.00736 -0.0431 0.8520 0.6018
-4.250 -0.2990 0.01325 0.00746 -0.0423 0.8483 0.6303
-4.000 -0.2746 0.01357 0.00778 -0.0413 0.8416 0.6491
-3.750 -0.2485 0.01381 0.00797 -0.0405 0.8366 0.6650
-3.500 -0.2223 0.01433 0.00849 -0.0391 0.8330 0.6851
-3.250 -0.1993 0.01518 0.00938 -0.0371 0.8273 0.7101
-3.000 -0.1732 0.01583 0.01008 -0.0354 0.8226 0.7225
-2.750 -0.1464 0.01587 0.01005 -0.0350 0.8187 0.7293
-2.500 -0.1192 0.01597 0.01008 -0.0346 0.8150 0.7345
-2.250 -0.0949 0.01590 0.00993 -0.0346 0.8089 0.7420
-2.000 -0.0678 0.01589 0.00989 -0.0343 0.8048 0.7453
-1.750 -0.0400 0.01587 0.00980 -0.0342 0.8016 0.7490
-1.500 -0.0139 0.01586 0.00974 -0.0342 0.7971 0.7537
-1.250 0.0118 0.01575 0.00957 -0.0345 0.7918 0.7591
-1.000 0.0391 0.01573 0.00953 -0.0344 0.7881 0.7620
-0.750 0.0671 0.01571 0.00947 -0.0344 0.7852 0.7656
-0.500 0.0929 0.01575 0.00950 -0.0345 0.7807 0.7701
-0.250 0.1190 0.01571 0.00943 -0.0348 0.7757 0.7753
0.000 0.1461 0.01572 0.00944 -0.0346 0.7721 0.7783
0.250 0.1741 0.01571 0.00942 -0.0346 0.7694 0.7820
0.500 0.2000 0.01579 0.00951 -0.0347 0.7651 0.7866
0.750 0.2258 0.01584 0.00957 -0.0349 0.7601 0.7918
1.000 0.2523 0.01589 0.00965 -0.0347 0.7566 0.7951
1.250 0.2805 0.01589 0.00965 -0.0348 0.7538 0.7990
1.500 0.3070 0.01598 0.00977 -0.0350 0.7500 0.8042
1.750 0.3311 0.01615 0.01000 -0.0348 0.7449 0.8089
2.000 0.3572 0.01622 0.01012 -0.0345 0.7411 0.8129
2.250 0.3857 0.01622 0.01013 -0.0347 0.7381 0.8176
2.500 0.4130 0.01632 0.01027 -0.0350 0.7345 0.8233
2.750 0.4347 0.01653 0.01060 -0.0341 0.7285 0.8274
3.000 0.4620 0.01650 0.01062 -0.0339 0.7242 0.8324
3.250 0.4932 0.01637 0.01049 -0.0345 0.7209 0.8385
3.500 0.5132 0.01658 0.01084 -0.0333 0.7136 0.8429
3.750 0.5407 0.01646 0.01077 -0.0330 0.7083 0.8481
4.000 0.5706 0.01626 0.01061 -0.0332 0.7025 0.8547
4.250 0.5954 0.01589 0.01032 -0.0319 0.6923 0.8593
4.500 0.6248 0.01493 0.00930 -0.0308 0.6750 0.8650
4.750 0.6510 0.01423 0.00857 -0.0296 0.6548 0.8715
5.000 0.6745 0.01390 0.00829 -0.0281 0.6406 0.8769
5.250 0.6981 0.01367 0.00812 -0.0271 0.6253 0.8846
5.500 0.7175 0.01346 0.00801 -0.0250 0.6059 0.8914
5.750 0.7381 0.01325 0.00784 -0.0233 0.5809 0.9000
6.000 0.7534 0.01311 0.00772 -0.0206 0.5414 0.9081
6.250 0.7596 0.01332 0.00754 -0.0163 0.4447 0.9191
6.500 0.7431 0.01453 0.00798 -0.0088 0.3085 0.9351
6.750 0.7247 0.01618 0.00888 -0.0020 0.1764 0.9568
7.000 0.7283 0.01837 0.01043 -0.0004 0.0856 0.9769
7.250 0.7490 0.01980 0.01179 -0.0015 0.0695 1.0000
7.500 0.7598 0.02057 0.01258 -0.0002 0.0639 1.0000
7.750 0.7688 0.02186 0.01380 0.0011 0.0591 1.0000
8.000 0.7855 0.02280 0.01477 0.0017 0.0553 1.0000
8.250 0.8016 0.02383 0.01579 0.0024 0.0523 1.0000
8.500 0.8178 0.02501 0.01692 0.0032 0.0500 1.0000
8.750 0.8400 0.02638 0.01825 0.0036 0.0480 1.0000
9.000 0.8643 0.02732 0.01925 0.0038 0.0464 1.0000
9.250 0.8885 0.02832 0.02029 0.0040 0.0442 1.0000
9.500 0.9152 0.02944 0.02143 0.0038 0.0425 1.0000
9.750 0.9495 0.03092 0.02290 0.0028 0.0412 1.0000
10.000 1.0172 0.03488 0.02696 -0.0032 0.0398 1.0000
10.250 1.0388 0.03665 0.02896 -0.0028 0.0395 1.0000
10.500 1.0539 0.03827 0.03084 -0.0014 0.0390 1.0000
10.750 1.0656 0.04005 0.03289 0.0002 0.0384 1.0000
11.000 1.0791 0.04253 0.03565 0.0015 0.0382 1.0000
11.250 1.0895 0.04553 0.03893 0.0029 0.0384 1.0000
11.500 1.0959 0.04884 0.04252 0.0045 0.0388 1.0000
11.750 1.1008 0.05301 0.04693 0.0059 0.0393 1.0000
12.000 1.1144 0.05570 0.04980 0.0069 0.0405 1.0000
12.250 1.0473 0.06262 0.05760 0.0146 0.0468 1.0000
12.500 0.9380 0.05869 0.05421 0.0206 0.0455 1.0000
12.750 0.9171 0.06435 0.06006 0.0212 0.0467 1.0000
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Polar data table (+)
Polar graphs
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