NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 500,000 Max Cl/Cd: 72.9 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662215-il-500000.txt Download as CSV file: xf-naca662215-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3611 0.08895 0.08659 -0.0757 0.9330 0.0329
-12.500 -0.4218 0.06901 0.06661 -0.0879 0.9350 0.0323
-12.250 -0.4984 0.05508 0.05240 -0.0944 0.9313 0.0315
-12.000 -0.5341 0.04925 0.04638 -0.0947 0.9243 0.0314
-11.750 -0.5576 0.04535 0.04233 -0.0936 0.9169 0.0315
-11.500 -0.5817 0.04176 0.03857 -0.0917 0.9097 0.0315
-11.250 -0.5965 0.03920 0.03587 -0.0895 0.9027 0.0317
-11.000 -0.7311 0.03891 0.03431 -0.0797 0.9020 0.0236
-10.750 -0.7382 0.03699 0.03212 -0.0753 0.8950 0.0236
-10.500 -0.7397 0.03495 0.02979 -0.0717 0.8887 0.0238
-10.250 -0.7422 0.03453 0.02902 -0.0674 0.8831 0.0242
-10.000 -0.7337 0.03168 0.02590 -0.0654 0.8787 0.0243
-9.750 -0.7194 0.02936 0.02335 -0.0639 0.8746 0.0243
-9.500 -0.6998 0.02669 0.02043 -0.0634 0.8714 0.0245
-9.250 -0.6747 0.02457 0.01816 -0.0637 0.8688 0.0250
-9.000 -0.6508 0.02337 0.01687 -0.0636 0.8660 0.0254
-8.750 -0.6276 0.02251 0.01597 -0.0634 0.8628 0.0261
-8.500 -0.6038 0.02169 0.01509 -0.0632 0.8596 0.0268
-8.250 -0.5792 0.02086 0.01417 -0.0630 0.8567 0.0276
-8.000 -0.5520 0.01992 0.01312 -0.0632 0.8541 0.0282
-7.750 -0.5254 0.01916 0.01225 -0.0633 0.8517 0.0289
-7.500 -0.5001 0.01856 0.01157 -0.0632 0.8492 0.0294
-7.250 -0.4691 0.01753 0.01050 -0.0642 0.8470 0.0302
-7.000 -0.4437 0.01645 0.00945 -0.0643 0.8445 0.0314
-6.750 -0.4245 0.01595 0.00894 -0.0632 0.8417 0.0325
-6.500 -0.4057 0.01555 0.00851 -0.0619 0.8391 0.0337
-6.250 -0.3876 0.01515 0.00806 -0.0604 0.8368 0.0349
-6.000 -0.3695 0.01481 0.00767 -0.0589 0.8344 0.0359
-5.750 -0.3509 0.01443 0.00727 -0.0576 0.8320 0.0369
-5.500 -0.3370 0.01379 0.00661 -0.0554 0.8292 0.0387
-5.250 -0.3179 0.01342 0.00624 -0.0542 0.8268 0.0407
-5.000 -0.2969 0.01313 0.00593 -0.0532 0.8246 0.0431
-4.750 -0.2748 0.01289 0.00563 -0.0524 0.8226 0.0450
-4.500 -0.2550 0.01250 0.00523 -0.0512 0.8206 0.0494
-4.250 -0.2325 0.01230 0.00501 -0.0505 0.8187 0.0545
-4.000 -0.2137 0.01186 0.00474 -0.0492 0.8167 0.0826
-3.750 -0.2121 0.01046 0.00425 -0.0453 0.8140 0.2890
-3.500 -0.2114 0.00897 0.00373 -0.0413 0.8113 0.5148
-3.250 -0.1967 0.00847 0.00384 -0.0388 0.8093 0.6711
-3.000 -0.1700 0.00857 0.00395 -0.0386 0.8079 0.7005
-2.750 -0.1426 0.00873 0.00410 -0.0385 0.8065 0.7197
-2.500 -0.1151 0.00896 0.00433 -0.0383 0.8052 0.7361
-2.250 -0.0874 0.00925 0.00460 -0.0380 0.8039 0.7498
-2.000 -0.0604 0.00953 0.00486 -0.0378 0.8023 0.7612
-1.750 -0.0327 0.00982 0.00523 -0.0375 0.8008 0.7690
-1.500 -0.0057 0.01001 0.00539 -0.0375 0.7992 0.7764
-1.250 0.0220 0.01020 0.00563 -0.0373 0.7976 0.7813
-1.000 0.0498 0.01037 0.00581 -0.0374 0.7961 0.7856
-0.750 0.0777 0.01042 0.00584 -0.0376 0.7946 0.7889
-0.500 0.1058 0.01044 0.00583 -0.0380 0.7930 0.7921
-0.250 0.1339 0.01044 0.00582 -0.0383 0.7917 0.7943
0.000 0.1624 0.01046 0.00585 -0.0386 0.7905 0.7960
0.250 0.1913 0.01047 0.00584 -0.0390 0.7890 0.7974
0.500 0.2201 0.01049 0.00585 -0.0394 0.7871 0.7986
0.750 0.2467 0.01049 0.00589 -0.0395 0.7844 0.8001
1.000 0.2740 0.01049 0.00590 -0.0397 0.7814 0.8019
1.250 0.3023 0.01045 0.00587 -0.0400 0.7787 0.8035
1.500 0.3311 0.01040 0.00583 -0.0405 0.7766 0.8051
1.750 0.3604 0.01037 0.00579 -0.0410 0.7747 0.8066
2.000 0.3909 0.01027 0.00566 -0.0417 0.7713 0.8080
2.250 0.4171 0.01003 0.00546 -0.0414 0.7636 0.8095
2.500 0.4476 0.00977 0.00517 -0.0418 0.7581 0.8108
2.750 0.4742 0.00962 0.00507 -0.0416 0.7509 0.8122
3.000 0.5038 0.00934 0.00476 -0.0417 0.7421 0.8136
3.250 0.5295 0.00915 0.00462 -0.0412 0.7315 0.8152
3.500 0.5558 0.00894 0.00443 -0.0408 0.7189 0.8168
3.750 0.5811 0.00878 0.00427 -0.0403 0.7030 0.8186
4.000 0.6059 0.00867 0.00417 -0.0397 0.6836 0.8206
4.250 0.6291 0.00863 0.00410 -0.0388 0.6537 0.8226
4.500 0.6354 0.00908 0.00405 -0.0346 0.5455 0.8251
4.750 0.6272 0.01013 0.00455 -0.0280 0.4290 0.8279
5.000 0.6163 0.01116 0.00509 -0.0210 0.3215 0.8311
5.250 0.6046 0.01223 0.00567 -0.0142 0.2184 0.8351
5.500 0.5959 0.01363 0.00646 -0.0084 0.1001 0.8391
5.750 0.6034 0.01447 0.00704 -0.0055 0.0551 0.8420
6.000 0.6193 0.01492 0.00749 -0.0037 0.0477 0.8445
6.250 0.6347 0.01543 0.00800 -0.0020 0.0428 0.8473
6.500 0.6511 0.01592 0.00854 -0.0004 0.0400 0.8504
6.750 0.6684 0.01639 0.00904 0.0009 0.0379 0.8537
7.250 0.6938 0.01781 0.01052 0.0049 0.0338 0.8603
7.500 0.7104 0.01832 0.01110 0.0063 0.0326 0.8636
7.750 0.7268 0.01887 0.01170 0.0077 0.0313 0.8676
8.000 0.7428 0.01950 0.01234 0.0090 0.0299 0.8718
8.250 0.7571 0.02017 0.01306 0.0106 0.0288 0.8757
8.500 0.7686 0.02117 0.01408 0.0126 0.0276 0.8799
8.750 0.7843 0.02214 0.01511 0.0140 0.0269 0.8843
9.000 0.8033 0.02276 0.01579 0.0149 0.0264 0.8887
9.250 0.8214 0.02341 0.01653 0.0160 0.0257 0.8929
9.500 0.8401 0.02407 0.01726 0.0170 0.0249 0.8978
9.750 0.8593 0.02476 0.01798 0.0177 0.0241 0.9031
10.000 0.8779 0.02548 0.01876 0.0187 0.0234 0.9081
10.250 0.8982 0.02629 0.01960 0.0194 0.0229 0.9138
10.500 0.9440 0.02831 0.02164 0.0166 0.0219 0.9149
10.750 0.9604 0.02915 0.02263 0.0179 0.0217 0.9214
11.000 0.9759 0.03007 0.02372 0.0193 0.0214 0.9293
11.250 0.9919 0.03122 0.02506 0.0207 0.0210 0.9378
11.500 1.0098 0.03270 0.02675 0.0217 0.0208 0.9476
11.750 1.0282 0.03457 0.02886 0.0223 0.0206 0.9596
12.000 1.0481 0.03656 0.03110 0.0216 0.0202 0.9741
12.250 1.0601 0.03849 0.03324 0.0221 0.0197 1.0000
12.500 1.0654 0.04096 0.03593 0.0235 0.0195 1.0000
12.750 1.0640 0.04393 0.03917 0.0255 0.0196 1.0000
13.000 1.0566 0.04729 0.04281 0.0278 0.0197 1.0000
13.250 1.0397 0.05165 0.04748 0.0305 0.0201 1.0000
13.500 1.0248 0.05531 0.05137 0.0325 0.0202 1.0000
13.750 1.0035 0.05986 0.05615 0.0342 0.0206 1.0000
14.000 0.9836 0.06421 0.06069 0.0352 0.0208 1.0000
14.250 0.9626 0.06898 0.06564 0.0356 0.0211 1.0000
14.500 0.8449 0.07164 0.06876 0.0372 0.0228 1.0000
14.750 0.8329 0.07620 0.07339 0.0360 0.0227 1.0000
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