NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63A210 (naca63a210-il) Reynolds number: 500,000 Max Cl/Cd: 58.29 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63a210-il-500000-n5.txt Download as CSV file: xf-naca63a210-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6337 0.10321 0.09934 -0.0054 0.4645 0.0077
-10.750 -0.8334 0.04821 0.04408 -0.0427 0.4658 0.0069
-10.500 -0.8484 0.04417 0.03978 -0.0420 0.4661 0.0070
-10.250 -0.8449 0.04150 0.03690 -0.0417 0.4661 0.0071
-10.000 -0.8384 0.03883 0.03398 -0.0412 0.4661 0.0073
-9.750 -0.8292 0.03618 0.03105 -0.0406 0.4660 0.0075
-9.500 -0.8174 0.03364 0.02821 -0.0400 0.4659 0.0078
-9.250 -0.8034 0.03122 0.02544 -0.0393 0.4658 0.0081
-9.000 -0.7871 0.02902 0.02291 -0.0386 0.4657 0.0084
-8.750 -0.7685 0.02713 0.02072 -0.0379 0.4656 0.0088
-8.500 -0.7482 0.02553 0.01885 -0.0373 0.4655 0.0092
-8.250 -0.7263 0.02426 0.01734 -0.0368 0.4655 0.0096
-8.000 -0.7026 0.02351 0.01641 -0.0365 0.4654 0.0099
-7.750 -0.6818 0.02187 0.01457 -0.0359 0.4654 0.0106
-7.500 -0.6578 0.02120 0.01382 -0.0356 0.4654 0.0112
-7.250 -0.6334 0.02052 0.01302 -0.0353 0.4653 0.0116
-7.000 -0.6090 0.01982 0.01222 -0.0350 0.4653 0.0121
-6.750 -0.5844 0.01913 0.01142 -0.0346 0.4654 0.0126
-6.500 -0.5597 0.01848 0.01066 -0.0343 0.4654 0.0132
-6.250 -0.5347 0.01788 0.00996 -0.0339 0.4654 0.0138
-6.000 -0.5092 0.01741 0.00938 -0.0337 0.4655 0.0143
-5.750 -0.4843 0.01681 0.00870 -0.0333 0.4655 0.0151
-5.500 -0.4595 0.01617 0.00800 -0.0330 0.4656 0.0162
-5.250 -0.4337 0.01576 0.00753 -0.0328 0.4656 0.0171
-5.000 -0.4075 0.01540 0.00712 -0.0326 0.4657 0.0180
-4.750 -0.3812 0.01507 0.00672 -0.0324 0.4658 0.0190
-4.500 -0.3547 0.01477 0.00636 -0.0323 0.4658 0.0203
-4.250 -0.3279 0.01449 0.00602 -0.0322 0.4654 0.0218
-4.000 -0.3013 0.01409 0.00559 -0.0320 0.4646 0.0261
-3.750 -0.2741 0.01381 0.00525 -0.0319 0.4637 0.0306
-3.500 -0.2472 0.01352 0.00497 -0.0319 0.4631 0.0403
-3.250 -0.2201 0.01328 0.00475 -0.0318 0.4629 0.0541
-3.000 -0.1933 0.01298 0.00453 -0.0318 0.4625 0.0786
-2.750 -0.1669 0.01257 0.00429 -0.0317 0.4620 0.1320
-2.500 -0.1421 0.01184 0.00400 -0.0316 0.4615 0.2564
-2.250 -0.1180 0.01107 0.00379 -0.0314 0.4612 0.4122
-2.000 -0.0916 0.01077 0.00370 -0.0313 0.4612 0.4798
-1.500 -0.0384 0.01034 0.00358 -0.0309 0.4609 0.5869
-1.250 -0.0116 0.01017 0.00353 -0.0307 0.4605 0.6303
-1.000 0.0158 0.01006 0.00348 -0.0305 0.4600 0.6583
-0.750 0.0434 0.00999 0.00344 -0.0305 0.4598 0.6778
-0.500 0.0713 0.00993 0.00340 -0.0304 0.4596 0.6923
-0.250 0.0992 0.00986 0.00334 -0.0304 0.4590 0.7039
0.000 0.1273 0.00979 0.00327 -0.0305 0.4581 0.7150
0.250 0.1554 0.00974 0.00323 -0.0305 0.4574 0.7264
0.500 0.1832 0.00969 0.00321 -0.0305 0.4571 0.7374
0.750 0.2112 0.00965 0.00321 -0.0305 0.4568 0.7483
1.250 0.2671 0.00955 0.00318 -0.0305 0.4550 0.7710
1.500 0.2950 0.00951 0.00317 -0.0306 0.4518 0.7822
1.750 0.3228 0.00953 0.00322 -0.0306 0.4484 0.7945
2.000 0.3501 0.00955 0.00333 -0.0305 0.4456 0.8076
2.250 0.3771 0.00960 0.00348 -0.0303 0.4410 0.8222
2.500 0.4036 0.00978 0.00373 -0.0301 0.4346 0.8397
2.750 0.4296 0.00975 0.00386 -0.0296 0.4249 0.8630
3.000 0.4559 0.00968 0.00394 -0.0291 0.4133 0.8949
3.250 0.4871 0.00958 0.00402 -0.0296 0.3917 0.9311
3.500 0.5222 0.00962 0.00370 -0.0312 0.3062 0.9621
3.750 0.5549 0.01009 0.00366 -0.0328 0.1867 0.9874
4.000 0.5846 0.01061 0.00386 -0.0338 0.1129 1.0000
4.250 0.6082 0.01102 0.00409 -0.0332 0.0723 1.0000
4.500 0.6326 0.01137 0.00434 -0.0327 0.0494 1.0000
4.750 0.6574 0.01169 0.00461 -0.0323 0.0360 1.0000
5.000 0.6824 0.01200 0.00490 -0.0319 0.0281 1.0000
5.250 0.7074 0.01233 0.00523 -0.0315 0.0229 1.0000
5.500 0.7321 0.01269 0.00561 -0.0310 0.0195 1.0000
5.750 0.7571 0.01303 0.00599 -0.0306 0.0179 1.0000
6.000 0.7817 0.01341 0.00640 -0.0301 0.0164 1.0000
6.250 0.8059 0.01384 0.00686 -0.0296 0.0153 1.0000
6.500 0.8290 0.01441 0.00750 -0.0288 0.0143 1.0000
6.750 0.8509 0.01512 0.00829 -0.0279 0.0136 1.0000
7.000 0.8739 0.01569 0.00894 -0.0272 0.0134 1.0000
7.250 0.8967 0.01625 0.00957 -0.0265 0.0130 1.0000
7.500 0.9194 0.01683 0.01023 -0.0258 0.0125 1.0000
7.750 0.9412 0.01751 0.01098 -0.0250 0.0121 1.0000
8.000 0.9626 0.01825 0.01183 -0.0241 0.0118 1.0000
8.250 0.9835 0.01904 0.01271 -0.0232 0.0114 1.0000
8.500 1.0041 0.01986 0.01363 -0.0222 0.0111 1.0000
8.750 1.0248 0.02066 0.01450 -0.0214 0.0108 1.0000
9.000 1.0457 0.02138 0.01529 -0.0206 0.0104 1.0000
9.250 1.0658 0.02219 0.01617 -0.0197 0.0099 1.0000
9.500 1.0814 0.02363 0.01773 -0.0183 0.0094 1.0000
9.750 1.0966 0.02519 0.01949 -0.0168 0.0091 1.0000
10.000 1.1147 0.02624 0.02070 -0.0157 0.0089 1.0000
10.250 1.1313 0.02747 0.02210 -0.0144 0.0087 1.0000
10.500 1.1461 0.02886 0.02368 -0.0130 0.0084 1.0000
10.750 1.1589 0.03043 0.02545 -0.0114 0.0082 1.0000
11.000 1.1694 0.03214 0.02737 -0.0097 0.0079 1.0000
11.250 1.1773 0.03398 0.02942 -0.0078 0.0077 1.0000
11.500 1.1811 0.03580 0.03144 -0.0054 0.0074 1.0000
11.750 1.1830 0.03763 0.03345 -0.0031 0.0073 1.0000
12.000 1.1842 0.03946 0.03544 -0.0012 0.0071 1.0000
12.250 1.1841 0.04148 0.03761 0.0002 0.0069 1.0000
12.500 1.1836 0.04370 0.03996 0.0011 0.0068 1.0000
12.750 1.1829 0.04611 0.04252 0.0015 0.0066 1.0000
13.000 1.1788 0.04924 0.04579 0.0010 0.0065 1.0000
13.250 1.1733 0.05299 0.04968 -0.0004 0.0065 1.0000
13.500 1.1627 0.05813 0.05499 -0.0032 0.0064 1.0000
13.750 1.1481 0.06423 0.06125 -0.0068 0.0064 1.0000
14.000 1.1267 0.07139 0.06860 -0.0108 0.0064 1.0000
14.250 1.0914 0.08211 0.07956 -0.0172 0.0064 1.0000
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