NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63A210 (naca63a210-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.44 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63a210-il-1000000-n5.txt Download as CSV file: xf-naca63a210-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63A210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9660 0.08120 0.07798 -0.0158 0.4369 0.0043
-14.000 -1.0470 0.05614 0.05258 -0.0341 0.4370 0.0040
-13.750 -1.0740 0.04779 0.04402 -0.0408 0.4371 0.0040
-13.500 -1.0913 0.04232 0.03834 -0.0442 0.4371 0.0040
-13.250 -1.1011 0.03852 0.03435 -0.0455 0.4372 0.0040
-13.000 -1.1047 0.03579 0.03143 -0.0451 0.4372 0.0041
-12.750 -1.1129 0.03299 0.02838 -0.0431 0.4372 0.0041
-12.500 -1.1094 0.03052 0.02565 -0.0419 0.4372 0.0043
-12.250 -1.0974 0.02887 0.02383 -0.0410 0.4373 0.0045
-12.000 -1.0810 0.02770 0.02253 -0.0404 0.4373 0.0046
-11.750 -1.0625 0.02673 0.02144 -0.0398 0.4374 0.0048
-11.500 -1.0427 0.02590 0.02051 -0.0394 0.4374 0.0049
-11.250 -1.0221 0.02511 0.01962 -0.0389 0.4375 0.0051
-11.000 -1.0012 0.02432 0.01870 -0.0385 0.4376 0.0052
-10.750 -0.9799 0.02352 0.01778 -0.0380 0.4376 0.0054
-10.500 -0.9583 0.02272 0.01686 -0.0376 0.4377 0.0056
-10.250 -0.9360 0.02201 0.01603 -0.0372 0.4377 0.0059
-10.000 -0.9131 0.02135 0.01526 -0.0369 0.4378 0.0061
-9.750 -0.8898 0.02074 0.01455 -0.0366 0.4379 0.0063
-9.500 -0.8660 0.02017 0.01387 -0.0363 0.4380 0.0065
-9.250 -0.8420 0.01962 0.01322 -0.0360 0.4380 0.0066
-9.000 -0.8204 0.01853 0.01198 -0.0355 0.4381 0.0069
-8.750 -0.7962 0.01794 0.01130 -0.0352 0.4382 0.0072
-8.500 -0.7712 0.01752 0.01082 -0.0350 0.4383 0.0075
-8.250 -0.7459 0.01713 0.01037 -0.0348 0.4383 0.0078
-8.000 -0.7206 0.01672 0.00990 -0.0346 0.4384 0.0082
-7.750 -0.6952 0.01630 0.00941 -0.0344 0.4385 0.0086
-7.500 -0.6696 0.01592 0.00897 -0.0343 0.4386 0.0090
-7.250 -0.6437 0.01559 0.00857 -0.0341 0.4387 0.0094
-7.000 -0.6176 0.01529 0.00821 -0.0340 0.4388 0.0097
-6.750 -0.5915 0.01496 0.00781 -0.0338 0.4389 0.0099
-6.500 -0.5664 0.01442 0.00718 -0.0335 0.4390 0.0103
-6.250 -0.5412 0.01388 0.00656 -0.0332 0.4391 0.0110
-6.000 -0.5150 0.01354 0.00619 -0.0331 0.4392 0.0116
-5.750 -0.4885 0.01327 0.00587 -0.0330 0.4393 0.0121
-5.500 -0.4619 0.01302 0.00559 -0.0329 0.4393 0.0127
-5.250 -0.4350 0.01280 0.00533 -0.0328 0.4391 0.0134
-5.000 -0.4081 0.01259 0.00508 -0.0328 0.4388 0.0140
-4.750 -0.3811 0.01238 0.00481 -0.0327 0.4385 0.0144
-4.500 -0.3540 0.01218 0.00458 -0.0326 0.4383 0.0147
-4.250 -0.3270 0.01194 0.00429 -0.0325 0.4381 0.0161
-4.000 -0.2998 0.01174 0.00409 -0.0325 0.4379 0.0181
-3.750 -0.2725 0.01159 0.00393 -0.0325 0.4376 0.0208
-3.500 -0.2452 0.01141 0.00376 -0.0324 0.4375 0.0269
-3.250 -0.2177 0.01128 0.00363 -0.0324 0.4375 0.0338
-3.000 -0.1903 0.01113 0.00351 -0.0324 0.4375 0.0433
-2.750 -0.1629 0.01097 0.00340 -0.0325 0.4375 0.0586
-2.500 -0.1357 0.01077 0.00328 -0.0325 0.4375 0.0865
-2.250 -0.1088 0.01049 0.00317 -0.0325 0.4375 0.1345
-2.000 -0.0822 0.01018 0.00306 -0.0324 0.4375 0.1977
-1.750 -0.0568 0.00961 0.00292 -0.0324 0.4373 0.3240
-1.500 -0.0308 0.00921 0.00284 -0.0323 0.4370 0.4224
-1.250 -0.0041 0.00897 0.00282 -0.0322 0.4365 0.4912
-1.000 0.0229 0.00879 0.00282 -0.0322 0.4361 0.5485
-0.750 0.0502 0.00868 0.00284 -0.0321 0.4356 0.5909
-0.500 0.0778 0.00862 0.00285 -0.0321 0.4354 0.6172
-0.250 0.1056 0.00859 0.00287 -0.0321 0.4352 0.6390
0.000 0.1336 0.00857 0.00290 -0.0322 0.4349 0.6555
0.250 0.1616 0.00857 0.00293 -0.0322 0.4348 0.6673
0.500 0.1898 0.00858 0.00296 -0.0323 0.4346 0.6784
0.750 0.2177 0.00858 0.00301 -0.0323 0.4336 0.6893
1.000 0.2457 0.00860 0.00306 -0.0323 0.4314 0.6995
1.250 0.2737 0.00863 0.00313 -0.0324 0.4293 0.7101
1.500 0.3016 0.00865 0.00319 -0.0324 0.4268 0.7206
1.750 0.3295 0.00868 0.00326 -0.0324 0.4235 0.7307
2.000 0.3574 0.00872 0.00334 -0.0325 0.4198 0.7411
2.250 0.3852 0.00871 0.00339 -0.0324 0.4127 0.7513
2.500 0.4133 0.00872 0.00347 -0.0324 0.3923 0.7615
2.750 0.4403 0.00886 0.00332 -0.0323 0.3297 0.7723
3.000 0.4667 0.00890 0.00303 -0.0321 0.2423 0.7831
3.250 0.4927 0.00909 0.00299 -0.0320 0.1688 0.7947
3.500 0.5186 0.00931 0.00303 -0.0318 0.1136 0.8080
3.750 0.5441 0.00955 0.00316 -0.0315 0.0699 0.8240
4.000 0.5698 0.00969 0.00332 -0.0311 0.0503 0.8458
4.250 0.5945 0.00979 0.00350 -0.0305 0.0381 0.8819
4.500 0.6197 0.00987 0.00369 -0.0299 0.0292 0.9368
4.750 0.6558 0.01009 0.00390 -0.0319 0.0224 0.9767
5.000 0.6899 0.01032 0.00413 -0.0335 0.0178 0.9972
5.250 0.7168 0.01058 0.00438 -0.0334 0.0147 1.0000
5.500 0.7424 0.01083 0.00464 -0.0331 0.0133 1.0000
5.750 0.7681 0.01108 0.00491 -0.0328 0.0126 1.0000
6.000 0.7936 0.01135 0.00521 -0.0324 0.0120 1.0000
6.250 0.8188 0.01165 0.00553 -0.0321 0.0114 1.0000
6.500 0.8439 0.01198 0.00589 -0.0317 0.0109 1.0000
6.750 0.8687 0.01234 0.00629 -0.0313 0.0104 1.0000
7.000 0.8929 0.01279 0.00678 -0.0307 0.0098 1.0000
7.250 0.9161 0.01336 0.00742 -0.0300 0.0094 1.0000
7.500 0.9392 0.01392 0.00806 -0.0293 0.0092 1.0000
7.750 0.9630 0.01437 0.00858 -0.0288 0.0091 1.0000
8.000 0.9869 0.01482 0.00908 -0.0283 0.0090 1.0000
8.250 1.0108 0.01525 0.00955 -0.0278 0.0088 1.0000
8.500 1.0345 0.01569 0.01005 -0.0273 0.0085 1.0000
8.750 1.0576 0.01621 0.01063 -0.0268 0.0083 1.0000
9.000 1.0801 0.01677 0.01125 -0.0261 0.0081 1.0000
9.250 1.1024 0.01735 0.01190 -0.0254 0.0079 1.0000
9.500 1.1244 0.01794 0.01257 -0.0247 0.0076 1.0000
9.750 1.1463 0.01853 0.01323 -0.0240 0.0074 1.0000
10.000 1.1682 0.01912 0.01388 -0.0234 0.0071 1.0000
10.250 1.1897 0.01972 0.01453 -0.0227 0.0069 1.0000
10.500 1.2108 0.02034 0.01521 -0.0220 0.0067 1.0000
10.750 1.2307 0.02108 0.01600 -0.0211 0.0064 1.0000
11.000 1.2446 0.02243 0.01749 -0.0195 0.0060 1.0000
11.250 1.2625 0.02329 0.01844 -0.0184 0.0059 1.0000
11.500 1.2823 0.02392 0.01917 -0.0175 0.0058 1.0000
11.750 1.3001 0.02470 0.02005 -0.0165 0.0057 1.0000
12.000 1.3167 0.02557 0.02101 -0.0153 0.0056 1.0000
12.250 1.3319 0.02650 0.02206 -0.0140 0.0054 1.0000
12.500 1.3454 0.02752 0.02318 -0.0125 0.0052 1.0000
12.750 1.3560 0.02856 0.02433 -0.0106 0.0051 1.0000
13.000 1.3643 0.02969 0.02558 -0.0085 0.0049 1.0000
13.250 1.3711 0.03093 0.02692 -0.0065 0.0048 1.0000
13.500 1.3770 0.03227 0.02837 -0.0047 0.0047 1.0000
13.750 1.3818 0.03377 0.02997 -0.0031 0.0046 1.0000
14.000 1.3856 0.03544 0.03175 -0.0018 0.0045 1.0000
14.250 1.3883 0.03735 0.03376 -0.0008 0.0044 1.0000
14.500 1.3893 0.03959 0.03613 -0.0002 0.0043 1.0000
14.750 1.3892 0.04217 0.03882 -0.0001 0.0042 1.0000
15.000 1.3874 0.04525 0.04202 -0.0006 0.0041 1.0000
15.250 1.3815 0.04926 0.04616 -0.0022 0.0041 1.0000
15.500 1.3736 0.05405 0.05109 -0.0047 0.0040 1.0000
15.750 1.3616 0.05936 0.05653 -0.0073 0.0040 1.0000
16.000 1.3438 0.06523 0.06253 -0.0098 0.0040 1.0000
16.250 1.3237 0.07221 0.06966 -0.0133 0.0040 1.0000
16.500 1.2959 0.08056 0.07817 -0.0176 0.0040 1.0000
16.750 1.2599 0.09129 0.08910 -0.0233 0.0040 1.0000
17.000 1.2006 0.10790 0.10595 -0.0323 0.0041 1.0000
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