NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 200,000 Max Cl/Cd: 46.05 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662215-il-200000-n5.txt Download as CSV file: xf-naca662215-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5789 0.08112 0.07723 -0.0743 1.0000 0.0216
-13.000 -0.6176 0.07191 0.06788 -0.0795 1.0000 0.0215
-12.750 -0.6474 0.06567 0.06148 -0.0818 0.9981 0.0214
-12.500 -0.6681 0.05928 0.05481 -0.0855 0.9762 0.0213
-12.250 -0.6841 0.05393 0.04913 -0.0879 0.9647 0.0215
-12.000 -0.6944 0.04965 0.04451 -0.0889 0.9539 0.0217
-11.750 -0.7027 0.04606 0.04056 -0.0885 0.9428 0.0220
-11.500 -0.7104 0.04314 0.03726 -0.0867 0.9323 0.0225
-11.250 -0.7177 0.04063 0.03437 -0.0839 0.9222 0.0228
-11.000 -0.7201 0.03855 0.03193 -0.0810 0.9137 0.0231
-10.750 -0.7200 0.03676 0.02979 -0.0779 0.9064 0.0233
-10.500 -0.7113 0.03475 0.02756 -0.0762 0.9009 0.0236
-10.250 -0.6987 0.03316 0.02581 -0.0747 0.8954 0.0239
-10.000 -0.6844 0.03181 0.02429 -0.0734 0.8908 0.0242
-9.750 -0.6683 0.03057 0.02290 -0.0722 0.8866 0.0246
-9.500 -0.6501 0.02935 0.02151 -0.0713 0.8820 0.0251
-9.250 -0.6306 0.02828 0.02030 -0.0705 0.8781 0.0258
-9.000 -0.6103 0.02731 0.01916 -0.0698 0.8748 0.0267
-8.750 -0.5872 0.02628 0.01794 -0.0695 0.8722 0.0276
-8.500 -0.5617 0.02525 0.01675 -0.0695 0.8689 0.0283
-8.250 -0.5350 0.02431 0.01565 -0.0697 0.8658 0.0289
-8.000 -0.5038 0.02306 0.01438 -0.0708 0.8636 0.0297
-7.750 -0.4795 0.02220 0.01352 -0.0707 0.8609 0.0306
-7.500 -0.4577 0.02152 0.01279 -0.0701 0.8583 0.0316
-7.250 -0.4371 0.02095 0.01218 -0.0693 0.8558 0.0330
-7.000 -0.4173 0.02039 0.01158 -0.0683 0.8522 0.0343
-6.750 -0.3983 0.01988 0.01100 -0.0672 0.8487 0.0356
-6.500 -0.3813 0.01931 0.01039 -0.0657 0.8456 0.0366
-6.250 -0.3676 0.01869 0.00975 -0.0637 0.8428 0.0379
-6.000 -0.3524 0.01823 0.00925 -0.0618 0.8405 0.0395
-5.750 -0.3360 0.01788 0.00888 -0.0602 0.8375 0.0416
-5.500 -0.3183 0.01756 0.00851 -0.0588 0.8345 0.0438
-5.250 -0.3010 0.01718 0.00809 -0.0573 0.8317 0.0463
-5.000 -0.2826 0.01682 0.00772 -0.0560 0.8292 0.0495
-4.750 -0.2627 0.01652 0.00736 -0.0548 0.8271 0.0544
-4.500 -0.2437 0.01614 0.00702 -0.0536 0.8253 0.0651
-4.250 -0.2280 0.01563 0.00669 -0.0518 0.8230 0.0994
-4.000 -0.2213 0.01479 0.00638 -0.0488 0.8192 0.2109
-3.750 -0.2184 0.01374 0.00601 -0.0451 0.8160 0.3583
-3.500 -0.2182 0.01262 0.00580 -0.0405 0.8131 0.5431
-3.250 -0.1988 0.01283 0.00653 -0.0380 0.8114 0.6805
-3.000 -0.1753 0.01314 0.00681 -0.0368 0.8099 0.7177
-2.750 -0.1482 0.01364 0.00731 -0.0360 0.8088 0.7387
-2.500 -0.1225 0.01407 0.00772 -0.0351 0.8072 0.7534
-2.250 -0.1005 0.01443 0.00804 -0.0339 0.8047 0.7657
-2.000 -0.0734 0.01482 0.00844 -0.0333 0.8024 0.7714
-1.750 -0.0491 0.01495 0.00853 -0.0328 0.8001 0.7779
-1.500 -0.0247 0.01494 0.00845 -0.0325 0.7983 0.7823
-1.250 0.0025 0.01502 0.00850 -0.0324 0.7968 0.7844
-1.000 0.0297 0.01507 0.00852 -0.0325 0.7954 0.7867
-0.750 0.0567 0.01509 0.00851 -0.0325 0.7941 0.7894
-0.500 0.0839 0.01506 0.00843 -0.0327 0.7929 0.7922
-0.250 0.1079 0.01506 0.00840 -0.0325 0.7908 0.7954
0.000 0.1287 0.01514 0.00849 -0.0318 0.7878 0.7980
0.250 0.1527 0.01524 0.00860 -0.0314 0.7852 0.7993
0.500 0.1783 0.01529 0.00867 -0.0313 0.7828 0.8009
0.750 0.2054 0.01529 0.00867 -0.0313 0.7807 0.8025
1.000 0.2338 0.01525 0.00863 -0.0317 0.7789 0.8040
1.250 0.2630 0.01519 0.00858 -0.0321 0.7774 0.8057
1.500 0.2871 0.01525 0.00867 -0.0318 0.7745 0.8077
1.750 0.3064 0.01540 0.00886 -0.0307 0.7696 0.8102
2.000 0.3327 0.01536 0.00885 -0.0308 0.7664 0.8127
2.250 0.3616 0.01528 0.00880 -0.0312 0.7640 0.8145
2.500 0.3917 0.01521 0.00878 -0.0317 0.7621 0.8157
2.750 0.4175 0.01525 0.00888 -0.0315 0.7590 0.8172
3.000 0.4360 0.01537 0.00909 -0.0300 0.7524 0.8192
3.250 0.4710 0.01490 0.00866 -0.0310 0.7471 0.8205
3.500 0.4947 0.01459 0.00841 -0.0300 0.7361 0.8226
3.750 0.5229 0.01407 0.00792 -0.0296 0.7229 0.8246
4.000 0.5481 0.01369 0.00758 -0.0288 0.7080 0.8269
4.250 0.5711 0.01335 0.00727 -0.0277 0.6870 0.8297
4.500 0.5882 0.01309 0.00701 -0.0252 0.6492 0.8318
4.750 0.6010 0.01305 0.00625 -0.0214 0.5121 0.8341
5.000 0.5942 0.01391 0.00660 -0.0152 0.4168 0.8378
5.250 0.5854 0.01474 0.00703 -0.0089 0.3387 0.8421
5.500 0.5814 0.01576 0.00766 -0.0041 0.2586 0.8464
5.750 0.5800 0.01687 0.00838 0.0003 0.1779 0.8496
6.000 0.5817 0.01802 0.00913 0.0038 0.1001 0.8533
6.250 0.5915 0.01889 0.00979 0.0061 0.0638 0.8571
6.500 0.6065 0.01954 0.01037 0.0076 0.0520 0.8610
6.750 0.6220 0.02008 0.01096 0.0092 0.0472 0.8642
7.000 0.6369 0.02067 0.01159 0.0108 0.0434 0.8679
7.250 0.6517 0.02132 0.01227 0.0124 0.0405 0.8720
7.500 0.6682 0.02192 0.01295 0.0136 0.0383 0.8763
7.750 0.6829 0.02257 0.01368 0.0150 0.0364 0.8800
8.000 0.6956 0.02333 0.01447 0.0168 0.0345 0.8843
8.250 0.7083 0.02418 0.01536 0.0184 0.0328 0.8893
8.500 0.7239 0.02490 0.01616 0.0197 0.0314 0.8942
8.750 0.7379 0.02566 0.01701 0.0212 0.0303 0.8990
9.000 0.7533 0.02646 0.01787 0.0224 0.0293 0.9047
9.250 0.7688 0.02731 0.01875 0.0236 0.0283 0.9106
9.500 0.7843 0.02821 0.01967 0.0248 0.0274 0.9170
9.750 0.8020 0.02922 0.02072 0.0257 0.0263 0.9239
10.000 0.8209 0.02999 0.02162 0.0264 0.0256 0.9310
10.250 0.8409 0.03087 0.02261 0.0270 0.0246 0.9391
10.500 0.8631 0.03184 0.02370 0.0271 0.0239 0.9474
10.750 0.8870 0.03292 0.02490 0.0267 0.0231 0.9567
11.000 0.9125 0.03412 0.02620 0.0259 0.0225 0.9677
11.250 0.9359 0.03534 0.02749 0.0253 0.0219 1.0000
11.500 0.9576 0.03677 0.02900 0.0252 0.0216 1.0000
11.750 0.9786 0.03858 0.03094 0.0252 0.0211 1.0000
12.000 0.9926 0.04037 0.03298 0.0259 0.0209 1.0000
12.250 1.0035 0.04235 0.03522 0.0268 0.0206 1.0000
12.500 1.0109 0.04451 0.03763 0.0280 0.0203 1.0000
12.750 1.0136 0.04677 0.04017 0.0294 0.0199 1.0000
13.000 1.0135 0.04931 0.04296 0.0308 0.0195 1.0000
13.250 1.0121 0.05185 0.04573 0.0321 0.0192 1.0000
13.500 1.0076 0.05469 0.04880 0.0333 0.0189 1.0000
13.750 0.9999 0.05788 0.05223 0.0344 0.0187 1.0000
14.000 0.9898 0.06138 0.05595 0.0352 0.0186 1.0000
14.250 0.9752 0.06553 0.06036 0.0357 0.0186 1.0000
14.500 0.9581 0.07008 0.06514 0.0356 0.0185 1.0000
14.750 0.9385 0.07526 0.07055 0.0348 0.0185 1.0000
15.000 0.9150 0.08144 0.07695 0.0330 0.0185 1.0000
15.250 0.8879 0.08893 0.08468 0.0298 0.0185 1.0000
15.500 0.8515 0.09928 0.09528 0.0241 0.0187 1.0000
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Polar data table (+)
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