NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 50,000 Max Cl/Cd: 32.93 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a210-il-50000-n5.txt Download as CSV file: xf-naca64a210-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5480 0.09764 0.09053 -0.0264 1.0000 0.0516
-9.500 -0.5503 0.09248 0.08542 -0.0294 1.0000 0.0509
-9.250 -0.5547 0.08677 0.07976 -0.0335 1.0000 0.0502
-9.000 -0.5631 0.08104 0.07407 -0.0378 1.0000 0.0495
-8.750 -0.5750 0.07614 0.06918 -0.0405 1.0000 0.0488
-8.500 -0.5846 0.07147 0.06445 -0.0423 1.0000 0.0484
-8.250 -0.5918 0.06708 0.05994 -0.0433 1.0000 0.0484
-8.000 -0.5961 0.06297 0.05565 -0.0435 1.0000 0.0487
-7.750 -0.5977 0.05908 0.05153 -0.0431 1.0000 0.0492
-7.500 -0.5968 0.05536 0.04752 -0.0423 1.0000 0.0497
-7.250 -0.5933 0.05179 0.04357 -0.0410 1.0000 0.0501
-7.000 -0.5870 0.04835 0.03977 -0.0395 1.0000 0.0501
-6.750 -0.5780 0.04511 0.03614 -0.0379 1.0000 0.0502
-6.500 -0.5665 0.04209 0.03269 -0.0362 1.0000 0.0506
-6.250 -0.5525 0.03930 0.02946 -0.0345 1.0000 0.0512
-6.000 -0.5363 0.03684 0.02652 -0.0329 1.0000 0.0526
-5.750 -0.5187 0.03474 0.02393 -0.0313 1.0000 0.0551
-5.500 -0.5003 0.03269 0.02180 -0.0302 1.0000 0.0580
-5.250 -0.4798 0.03090 0.01974 -0.0289 1.0000 0.0601
-5.000 -0.4581 0.02928 0.01790 -0.0276 1.0000 0.0625
-4.750 -0.4362 0.02793 0.01630 -0.0262 1.0000 0.0662
-4.500 -0.4161 0.02668 0.01504 -0.0249 1.0000 0.0722
-4.250 -0.3959 0.02564 0.01386 -0.0234 1.0000 0.0787
-4.000 -0.3766 0.02454 0.01269 -0.0219 1.0000 0.0851
-3.750 -0.3571 0.02359 0.01166 -0.0209 1.0000 0.0987
-3.500 -0.3367 0.02252 0.01062 -0.0201 1.0000 0.1187
-3.250 -0.3167 0.02093 0.00952 -0.0198 1.0000 0.1854
-3.000 -0.3056 0.01878 0.00944 -0.0169 1.0000 0.5728
-2.750 -0.2941 0.01872 0.00969 -0.0124 1.0000 0.7000
-2.500 -0.2866 0.01878 0.00995 -0.0063 1.0000 0.7960
-2.250 -0.2714 0.01898 0.01029 -0.0004 1.0000 0.8917
-2.000 -0.2249 0.01914 0.01014 -0.0034 1.0000 0.9366
-1.750 -0.1816 0.01913 0.00984 -0.0074 1.0000 0.9598
-1.500 -0.1306 0.01917 0.00956 -0.0132 0.9961 0.9806
-1.250 -0.0772 0.01922 0.00934 -0.0197 0.9897 1.0000
-1.000 -0.0434 0.01924 0.00915 -0.0227 0.9789 1.0000
-0.750 -0.0100 0.01931 0.00904 -0.0253 0.9684 1.0000
-0.500 0.0236 0.01943 0.00900 -0.0278 0.9584 1.0000
-0.250 0.0611 0.01960 0.00902 -0.0308 0.9501 1.0000
0.000 0.0921 0.01976 0.00907 -0.0324 0.9394 1.0000
0.250 0.1251 0.01996 0.00918 -0.0343 0.9300 1.0000
0.500 0.1632 0.02017 0.00933 -0.0371 0.9222 1.0000
0.750 0.1927 0.02040 0.00952 -0.0381 0.9119 1.0000
1.000 0.2261 0.02064 0.00974 -0.0399 0.9031 1.0000
1.250 0.2602 0.02088 0.00998 -0.0416 0.8947 1.0000
1.500 0.2882 0.02115 0.01029 -0.0422 0.8844 1.0000
1.750 0.3210 0.02140 0.01059 -0.0436 0.8763 1.0000
2.000 0.3503 0.02168 0.01093 -0.0443 0.8666 1.0000
2.250 0.3771 0.02201 0.01135 -0.0445 0.8565 1.0000
2.500 0.4104 0.02224 0.01170 -0.0457 0.8486 1.0000
2.750 0.4365 0.02258 0.01216 -0.0458 0.8379 1.0000
3.000 0.4626 0.02292 0.01267 -0.0457 0.8270 1.0000
3.250 0.4921 0.02318 0.01309 -0.0461 0.8169 1.0000
3.500 0.5238 0.02333 0.01345 -0.0466 0.8068 1.0000
3.750 0.5505 0.02354 0.01387 -0.0462 0.7936 1.0000
4.000 0.5793 0.02358 0.01419 -0.0458 0.7792 1.0000
4.250 0.6067 0.02326 0.01411 -0.0442 0.7564 1.0000
4.500 0.6366 0.02177 0.01277 -0.0405 0.7097 1.0000
4.750 0.6573 0.02076 0.01175 -0.0358 0.6421 1.0000
5.000 0.6750 0.02050 0.01140 -0.0319 0.5533 1.0000
5.250 0.6831 0.02147 0.01112 -0.0269 0.3212 1.0000
5.500 0.6838 0.02430 0.01260 -0.0238 0.1570 1.0000
5.750 0.6954 0.02626 0.01418 -0.0218 0.1150 1.0000
6.000 0.7104 0.02784 0.01567 -0.0201 0.0945 1.0000
6.250 0.7275 0.02931 0.01717 -0.0186 0.0821 1.0000
6.500 0.7478 0.03084 0.01882 -0.0174 0.0744 1.0000
6.750 0.7705 0.03232 0.02033 -0.0166 0.0662 1.0000
7.000 0.7995 0.03407 0.02225 -0.0161 0.0612 1.0000
7.250 0.8299 0.03609 0.02450 -0.0159 0.0576 1.0000
7.500 0.8557 0.03819 0.02671 -0.0157 0.0540 1.0000
7.750 0.8794 0.04070 0.02951 -0.0151 0.0508 1.0000
8.000 0.9007 0.04338 0.03269 -0.0141 0.0488 1.0000
8.250 0.9189 0.04645 0.03623 -0.0129 0.0477 1.0000
8.500 0.9328 0.04975 0.04000 -0.0114 0.0470 1.0000
8.750 0.9424 0.05326 0.04397 -0.0097 0.0465 1.0000
9.000 0.9477 0.05694 0.04809 -0.0079 0.0462 1.0000
9.250 0.9488 0.06066 0.05221 -0.0060 0.0458 1.0000
9.500 0.9459 0.06435 0.05625 -0.0042 0.0452 1.0000
9.750 0.9393 0.06805 0.06024 -0.0025 0.0446 1.0000
10.000 0.9279 0.07174 0.06417 -0.0009 0.0442 1.0000
10.250 0.9113 0.07565 0.06829 0.0004 0.0442 1.0000
10.500 0.8906 0.08030 0.07312 0.0004 0.0445 1.0000
10.750 0.8676 0.08591 0.07888 -0.0013 0.0452 1.0000
11.000 0.8437 0.09273 0.08581 -0.0050 0.0461 1.0000
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Polar data table (+)
Polar graphs
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