NACA 64-215 AIRFOIL (n64215-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-215 AIRFOIL (n64215-il) Reynolds number: 500,000 Max Cl/Cd: 85.51 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64215-il-500000.txt Download as CSV file: xf-n64215-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-215 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7782 0.09843 0.09564 -0.0345 1.0000 0.0213
-15.500 -0.8175 0.08636 0.08339 -0.0424 1.0000 0.0211
-15.250 -0.8464 0.07766 0.07453 -0.0477 1.0000 0.0208
-15.000 -0.8741 0.07010 0.06677 -0.0521 1.0000 0.0208
-14.750 -0.8988 0.06370 0.06018 -0.0553 1.0000 0.0207
-14.500 -0.9195 0.05832 0.05460 -0.0575 1.0000 0.0208
-14.250 -0.9382 0.05353 0.04959 -0.0589 1.0000 0.0208
-14.000 -0.9522 0.04946 0.04532 -0.0596 1.0000 0.0208
-13.750 -0.9632 0.04607 0.04172 -0.0598 1.0000 0.0210
-13.500 -0.9714 0.04296 0.03840 -0.0596 1.0000 0.0211
-13.250 -0.9767 0.04077 0.03601 -0.0589 1.0000 0.0214
-13.000 -0.9798 0.03841 0.03346 -0.0580 1.0000 0.0215
-12.750 -0.9832 0.03570 0.03053 -0.0567 1.0000 0.0218
-12.500 -0.9742 0.03368 0.02844 -0.0559 1.0000 0.0222
-12.250 -0.9649 0.03222 0.02692 -0.0550 1.0000 0.0225
-12.000 -0.9555 0.03090 0.02552 -0.0539 1.0000 0.0228
-11.750 -0.9459 0.02974 0.02429 -0.0526 1.0000 0.0232
-11.500 -0.9346 0.02861 0.02309 -0.0514 1.0000 0.0236
-11.250 -0.9230 0.02752 0.02191 -0.0499 1.0000 0.0240
-11.000 -0.9103 0.02638 0.02068 -0.0485 1.0000 0.0244
-10.750 -0.8981 0.02540 0.01961 -0.0469 1.0000 0.0249
-10.500 -0.8853 0.02449 0.01861 -0.0451 1.0000 0.0253
-10.250 -0.8734 0.02380 0.01784 -0.0432 1.0000 0.0257
-10.000 -0.8500 0.02245 0.01640 -0.0436 0.9923 0.0265
-9.750 -0.8165 0.02119 0.01516 -0.0459 0.9812 0.0274
-9.500 -0.7813 0.02027 0.01421 -0.0484 0.9698 0.0283
-9.250 -0.7481 0.01939 0.01326 -0.0505 0.9567 0.0293
-9.000 -0.7223 0.01867 0.01245 -0.0508 0.9400 0.0302
-8.750 -0.7025 0.01817 0.01184 -0.0498 0.9234 0.0309
-8.500 -0.6882 0.01731 0.01090 -0.0479 0.9082 0.0319
-8.250 -0.6725 0.01665 0.01019 -0.0462 0.8949 0.0332
-8.000 -0.6534 0.01618 0.00967 -0.0451 0.8831 0.0345
-7.750 -0.6334 0.01573 0.00915 -0.0440 0.8728 0.0359
-7.500 -0.6122 0.01535 0.00867 -0.0430 0.8629 0.0371
-7.250 -0.5948 0.01455 0.00783 -0.0417 0.8530 0.0391
-7.000 -0.5733 0.01412 0.00734 -0.0409 0.8445 0.0412
-6.750 -0.5497 0.01376 0.00693 -0.0404 0.8353 0.0437
-6.500 -0.5280 0.01325 0.00635 -0.0396 0.8273 0.0469
-6.250 -0.5040 0.01286 0.00595 -0.0392 0.8187 0.0509
-5.750 -0.4557 0.01205 0.00509 -0.0383 0.8033 0.0643
-5.500 -0.4322 0.01155 0.00466 -0.0379 0.7960 0.0841
-5.250 -0.4096 0.01084 0.00421 -0.0375 0.7881 0.1355
-5.000 -0.3884 0.00993 0.00370 -0.0371 0.7805 0.2282
-4.750 -0.3684 0.00875 0.00314 -0.0367 0.7730 0.3707
-4.500 -0.3435 0.00830 0.00299 -0.0365 0.7657 0.4626
-4.250 -0.3160 0.00820 0.00290 -0.0365 0.7591 0.4945
-4.000 -0.2878 0.00813 0.00283 -0.0365 0.7518 0.5153
-3.750 -0.2597 0.00812 0.00276 -0.0366 0.7455 0.5304
-3.500 -0.2311 0.00809 0.00271 -0.0367 0.7385 0.5432
-3.250 -0.2024 0.00810 0.00264 -0.0369 0.7318 0.5544
-3.000 -0.1741 0.00809 0.00263 -0.0369 0.7256 0.5670
-2.750 -0.1457 0.00810 0.00264 -0.0370 0.7187 0.5807
-2.500 -0.1175 0.00815 0.00265 -0.0370 0.7126 0.5937
-2.250 -0.0889 0.00819 0.00268 -0.0371 0.7059 0.6060
-2.000 -0.0603 0.00819 0.00266 -0.0372 0.6996 0.6129
-1.750 -0.0313 0.00822 0.00260 -0.0375 0.6940 0.6180
-1.500 -0.0024 0.00817 0.00257 -0.0377 0.6878 0.6231
-1.250 0.0263 0.00817 0.00255 -0.0379 0.6822 0.6283
-1.000 0.0553 0.00820 0.00252 -0.0381 0.6769 0.6333
-0.750 0.0844 0.00818 0.00249 -0.0384 0.6710 0.6380
-0.500 0.1131 0.00817 0.00248 -0.0386 0.6658 0.6424
-0.250 0.1420 0.00820 0.00248 -0.0388 0.6609 0.6472
0.000 0.1712 0.00821 0.00248 -0.0391 0.6553 0.6524
0.250 0.1999 0.00820 0.00248 -0.0393 0.6502 0.6570
0.500 0.2287 0.00825 0.00251 -0.0396 0.6457 0.6622
0.750 0.2578 0.00827 0.00255 -0.0399 0.6409 0.6681
1.000 0.2866 0.00827 0.00259 -0.0401 0.6362 0.6735
1.250 0.3154 0.00832 0.00263 -0.0403 0.6320 0.6791
1.500 0.3444 0.00838 0.00270 -0.0406 0.6276 0.6852
1.750 0.3731 0.00838 0.00276 -0.0408 0.6225 0.6908
2.000 0.4017 0.00841 0.00281 -0.0409 0.6174 0.6969
2.500 0.4591 0.00850 0.00298 -0.0413 0.6078 0.7094
2.750 0.4877 0.00854 0.00305 -0.0415 0.6026 0.7163
3.000 0.5159 0.00859 0.00310 -0.0416 0.5954 0.7230
3.250 0.5436 0.00857 0.00313 -0.0415 0.5854 0.7299
3.500 0.5716 0.00859 0.00317 -0.0416 0.5749 0.7374
3.750 0.5989 0.00862 0.00322 -0.0414 0.5642 0.7440
4.000 0.6264 0.00864 0.00326 -0.0413 0.5507 0.7516
4.250 0.6539 0.00866 0.00336 -0.0413 0.5395 0.7585
4.500 0.6814 0.00873 0.00346 -0.0412 0.5290 0.7661
4.750 0.7085 0.00882 0.00356 -0.0411 0.5166 0.7734
5.000 0.7353 0.00890 0.00369 -0.0409 0.5017 0.7810
5.250 0.7619 0.00901 0.00383 -0.0407 0.4814 0.7890
5.500 0.7867 0.00920 0.00399 -0.0402 0.4502 0.7969
5.750 0.8063 0.00980 0.00427 -0.0390 0.3696 0.8056
6.000 0.8186 0.01101 0.00497 -0.0369 0.2644 0.8143
6.250 0.8327 0.01209 0.00565 -0.0352 0.1834 0.8233
6.500 0.8476 0.01302 0.00628 -0.0335 0.1235 0.8328
6.750 0.8634 0.01379 0.00687 -0.0318 0.0849 0.8420
7.000 0.8804 0.01447 0.00745 -0.0303 0.0638 0.8527
7.250 0.8972 0.01501 0.00799 -0.0286 0.0537 0.8633
7.500 0.9128 0.01558 0.00856 -0.0267 0.0475 0.8750
7.750 0.9296 0.01600 0.00907 -0.0250 0.0440 0.8879
8.000 0.9425 0.01651 0.00962 -0.0226 0.0409 0.9032
8.250 0.9477 0.01704 0.01024 -0.0188 0.0388 0.9251
8.500 0.9603 0.01742 0.01075 -0.0164 0.0368 0.9603
8.750 0.9814 0.01813 0.01146 -0.0164 0.0346 1.0000
9.000 0.9892 0.01927 0.01260 -0.0144 0.0327 1.0000
9.250 1.0051 0.01997 0.01336 -0.0134 0.0315 1.0000
9.500 1.0195 0.02076 0.01418 -0.0122 0.0300 1.0000
9.750 1.0316 0.02171 0.01515 -0.0109 0.0290 1.0000
10.000 1.0398 0.02298 0.01641 -0.0093 0.0279 1.0000
10.250 1.0467 0.02441 0.01789 -0.0077 0.0271 1.0000
10.500 1.0601 0.02541 0.01896 -0.0067 0.0266 1.0000
10.750 1.0729 0.02648 0.02009 -0.0057 0.0257 1.0000
11.000 1.0851 0.02763 0.02128 -0.0048 0.0250 1.0000
11.250 1.0969 0.02882 0.02251 -0.0039 0.0245 1.0000
11.500 1.1085 0.03006 0.02377 -0.0030 0.0239 1.0000
11.750 1.1187 0.03148 0.02520 -0.0021 0.0232 1.0000
12.000 1.1289 0.03315 0.02691 -0.0010 0.0226 1.0000
12.250 1.1412 0.03440 0.02825 -0.0003 0.0222 1.0000
12.500 1.1533 0.03575 0.02969 0.0004 0.0218 1.0000
12.750 1.1650 0.03717 0.03120 0.0010 0.0214 1.0000
13.000 1.1763 0.03868 0.03279 0.0017 0.0210 1.0000
13.250 1.1868 0.04024 0.03443 0.0022 0.0206 1.0000
13.500 1.1970 0.04190 0.03618 0.0028 0.0203 1.0000
13.750 1.2058 0.04362 0.03797 0.0032 0.0199 1.0000
14.000 1.2145 0.04544 0.03986 0.0036 0.0197 1.0000
14.250 1.2229 0.04733 0.04183 0.0039 0.0195 1.0000
14.500 1.2307 0.04932 0.04388 0.0042 0.0192 1.0000
14.750 1.2386 0.05157 0.04621 0.0045 0.0189 1.0000
15.000 1.2444 0.05460 0.04939 0.0049 0.0187 1.0000
15.250 1.2410 0.05779 0.05276 0.0048 0.0185 1.0000
15.500 1.2376 0.06096 0.05611 0.0045 0.0184 1.0000
15.750 1.2326 0.06448 0.05981 0.0038 0.0183 1.0000
16.000 1.2250 0.06847 0.06399 0.0028 0.0181 1.0000
16.250 1.2159 0.07302 0.06874 0.0016 0.0181 1.0000
16.500 1.2051 0.07792 0.07383 -0.0002 0.0179 1.0000
16.750 1.1922 0.08332 0.07943 -0.0024 0.0178 1.0000
17.000 1.1757 0.08967 0.08598 -0.0052 0.0178 1.0000
17.250 1.1573 0.09666 0.09318 -0.0087 0.0179 1.0000
17.500 1.1359 0.10454 0.10127 -0.0130 0.0178 1.0000
17.750 1.1111 0.11363 0.11056 -0.0183 0.0179 1.0000
18.000 1.0823 0.12426 0.12141 -0.0251 0.0180 1.0000
18.250 1.0450 0.13773 0.13510 -0.0339 0.0182 1.0000
18.500 0.9934 0.15630 0.15390 -0.0460 0.0185 1.0000
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