NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 200,000 Max Cl/Cd: 54.05 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64210-il-200000-n5.txt Download as CSV file: xf-naca64210-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-210
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5901 0.08787 0.08426 -0.0228 1.0000 0.0159
-10.250 -0.5981 0.08071 0.07716 -0.0273 1.0000 0.0158
-10.000 -0.6122 0.07136 0.06779 -0.0346 1.0000 0.0157
-9.750 -0.6291 0.06478 0.06116 -0.0398 1.0000 0.0155
-9.500 -0.6482 0.05958 0.05586 -0.0427 1.0000 0.0154
-9.250 -0.6665 0.05543 0.05158 -0.0429 1.0000 0.0153
-9.000 -0.6792 0.05047 0.04637 -0.0429 1.0000 0.0154
-8.750 -0.6866 0.04550 0.04106 -0.0423 1.0000 0.0155
-8.500 -0.6885 0.04078 0.03591 -0.0412 1.0000 0.0157
-8.250 -0.6848 0.03663 0.03126 -0.0399 1.0000 0.0159
-8.000 -0.6773 0.03295 0.02721 -0.0387 1.0000 0.0163
-7.750 -0.6637 0.03068 0.02471 -0.0376 1.0000 0.0167
-7.500 -0.6476 0.02915 0.02299 -0.0366 1.0000 0.0174
-7.250 -0.6307 0.02789 0.02156 -0.0355 1.0000 0.0183
-7.000 -0.6138 0.02655 0.02002 -0.0342 1.0000 0.0195
-6.750 -0.5976 0.02481 0.01798 -0.0325 1.0000 0.0203
-6.500 -0.5689 0.02284 0.01567 -0.0333 0.9951 0.0211
-6.250 -0.5362 0.02126 0.01380 -0.0346 0.9886 0.0219
-6.000 -0.5042 0.01955 0.01192 -0.0361 0.9826 0.0235
-5.750 -0.4713 0.01856 0.01088 -0.0377 0.9762 0.0252
-5.500 -0.4397 0.01750 0.00973 -0.0388 0.9684 0.0264
-5.250 -0.4071 0.01653 0.00867 -0.0401 0.9615 0.0280
-5.000 -0.3758 0.01570 0.00772 -0.0411 0.9531 0.0298
-4.750 -0.3449 0.01497 0.00692 -0.0420 0.9445 0.0318
-4.500 -0.3143 0.01417 0.00611 -0.0430 0.9361 0.0361
-4.250 -0.2854 0.01364 0.00548 -0.0434 0.9259 0.0399
-4.000 -0.2566 0.01315 0.00490 -0.0438 0.9164 0.0446
-3.750 -0.2281 0.01271 0.00443 -0.0441 0.9069 0.0543
-3.500 -0.2015 0.01222 0.00401 -0.0440 0.8963 0.0736
-3.250 -0.1765 0.01137 0.00355 -0.0441 0.8860 0.1704
-3.000 -0.1545 0.01003 0.00315 -0.0440 0.8762 0.4012
-2.750 -0.1300 0.00960 0.00310 -0.0434 0.8661 0.5226
-2.500 -0.1042 0.00944 0.00307 -0.0428 0.8564 0.5805
-2.250 -0.0794 0.00935 0.00314 -0.0418 0.8475 0.6470
-2.000 -0.0547 0.00935 0.00324 -0.0407 0.8376 0.6914
-1.750 -0.0280 0.00934 0.00319 -0.0403 0.8285 0.7070
-1.500 -0.0007 0.00932 0.00310 -0.0400 0.8200 0.7177
-1.250 0.0265 0.00929 0.00303 -0.0397 0.8106 0.7257
-1.000 0.0540 0.00928 0.00295 -0.0396 0.8020 0.7346
-0.750 0.0811 0.00927 0.00291 -0.0393 0.7930 0.7430
-0.500 0.1085 0.00926 0.00288 -0.0391 0.7845 0.7518
-0.250 0.1359 0.00927 0.00285 -0.0389 0.7764 0.7607
0.000 0.1630 0.00927 0.00286 -0.0387 0.7674 0.7694
0.250 0.1902 0.00929 0.00286 -0.0385 0.7594 0.7791
0.500 0.2172 0.00931 0.00289 -0.0382 0.7507 0.7884
0.750 0.2443 0.00933 0.00293 -0.0380 0.7431 0.7975
1.000 0.2714 0.00936 0.00298 -0.0377 0.7349 0.8077
1.250 0.2980 0.00940 0.00305 -0.0374 0.7268 0.8175
1.500 0.3246 0.00944 0.00312 -0.0370 0.7192 0.8275
1.750 0.3514 0.00948 0.00322 -0.0367 0.7113 0.8380
2.000 0.3777 0.00953 0.00332 -0.0362 0.7034 0.8487
2.250 0.4035 0.00957 0.00343 -0.0356 0.6931 0.8595
2.500 0.4292 0.00962 0.00353 -0.0350 0.6830 0.8708
2.750 0.4543 0.00965 0.00360 -0.0342 0.6676 0.8829
3.000 0.4774 0.00967 0.00355 -0.0328 0.6320 0.8958
3.250 0.4997 0.00977 0.00349 -0.0314 0.5797 0.9099
3.500 0.5237 0.00992 0.00355 -0.0304 0.5385 0.9250
3.750 0.5486 0.01015 0.00365 -0.0298 0.4833 0.9413
4.000 0.5704 0.01113 0.00391 -0.0292 0.3180 0.9619
4.250 0.5955 0.01260 0.00459 -0.0301 0.1517 1.0000
4.500 0.6162 0.01362 0.00519 -0.0295 0.0759 1.0000
4.750 0.6398 0.01429 0.00573 -0.0292 0.0529 1.0000
5.000 0.6641 0.01487 0.00632 -0.0289 0.0432 1.0000
5.250 0.6876 0.01555 0.00701 -0.0285 0.0371 1.0000
5.500 0.7112 0.01622 0.00775 -0.0280 0.0340 1.0000
5.750 0.7346 0.01688 0.00848 -0.0276 0.0310 1.0000
6.000 0.7574 0.01762 0.00926 -0.0271 0.0280 1.0000
6.250 0.7773 0.01879 0.01044 -0.0262 0.0258 1.0000
6.500 0.8000 0.01964 0.01139 -0.0255 0.0248 1.0000
6.750 0.8223 0.02063 0.01247 -0.0249 0.0237 1.0000
7.000 0.8449 0.02174 0.01366 -0.0242 0.0228 1.0000
7.250 0.8676 0.02295 0.01499 -0.0236 0.0219 1.0000
7.500 0.8906 0.02425 0.01641 -0.0230 0.0211 1.0000
7.750 0.9132 0.02540 0.01766 -0.0226 0.0202 1.0000
8.000 0.9348 0.02666 0.01898 -0.0221 0.0192 1.0000
8.250 0.9552 0.02891 0.02140 -0.0215 0.0183 1.0000
8.500 0.9759 0.03068 0.02345 -0.0207 0.0179 1.0000
8.750 0.9945 0.03282 0.02596 -0.0198 0.0175 1.0000
9.000 1.0101 0.03538 0.02890 -0.0185 0.0170 1.0000
9.250 1.0228 0.03804 0.03195 -0.0171 0.0164 1.0000
9.500 1.0328 0.04064 0.03490 -0.0155 0.0156 1.0000
9.750 1.0419 0.04278 0.03729 -0.0141 0.0149 1.0000
10.000 1.0474 0.04519 0.03995 -0.0125 0.0145 1.0000
10.250 1.0469 0.04809 0.04312 -0.0106 0.0142 1.0000
10.500 1.0407 0.05081 0.04607 -0.0081 0.0140 1.0000
10.750 1.0288 0.05390 0.04939 -0.0058 0.0139 1.0000
11.000 1.0147 0.05732 0.05302 -0.0045 0.0138 1.0000
11.250 0.9954 0.06179 0.05772 -0.0042 0.0138 1.0000
11.500 0.9752 0.06683 0.06296 -0.0054 0.0138 1.0000
11.750 0.9483 0.07378 0.07014 -0.0084 0.0139 1.0000
12.000 0.8925 0.08877 0.08543 -0.0180 0.0144 1.0000
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Polar data table (+)
Polar graphs
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