NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA 64-012A AIRFOIL (n64012a-il) Reynolds number: 50,000 Max Cl/Cd: 27.23 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64012a-il-50000-n5.txt Download as CSV file: xf-n64012a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-012A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7891 0.07868 0.07096 -0.0314 1.0000 0.0480
-10.750 -0.8055 0.07444 0.06657 -0.0317 1.0000 0.0479
-10.500 -0.8210 0.07066 0.06261 -0.0307 1.0000 0.0478
-10.250 -0.8336 0.06707 0.05879 -0.0292 1.0000 0.0478
-10.000 -0.8424 0.06345 0.05487 -0.0276 1.0000 0.0479
-9.750 -0.8458 0.05986 0.05104 -0.0261 1.0000 0.0484
-9.500 -0.8413 0.05674 0.04774 -0.0250 1.0000 0.0496
-9.250 -0.8334 0.05409 0.04495 -0.0238 1.0000 0.0510
-9.000 -0.8262 0.05132 0.04191 -0.0224 1.0000 0.0525
-8.750 -0.8173 0.04843 0.03867 -0.0208 1.0000 0.0537
-8.500 -0.8051 0.04552 0.03537 -0.0193 1.0000 0.0546
-8.250 -0.7893 0.04277 0.03223 -0.0180 1.0000 0.0558
-8.000 -0.7701 0.04025 0.02930 -0.0169 1.0000 0.0573
-7.750 -0.7492 0.03811 0.02673 -0.0159 1.0000 0.0600
-7.500 -0.7265 0.03617 0.02483 -0.0155 1.0000 0.0637
-7.250 -0.7013 0.03445 0.02295 -0.0149 1.0000 0.0677
-7.000 -0.6731 0.03286 0.02108 -0.0144 1.0000 0.0718
-6.750 -0.6507 0.03140 0.01973 -0.0136 1.0000 0.0781
-6.500 -0.6286 0.03021 0.01833 -0.0124 1.0000 0.0858
-6.250 -0.6123 0.02886 0.01707 -0.0108 1.0000 0.0936
-6.000 -0.5979 0.02764 0.01587 -0.0089 1.0000 0.1057
-5.750 -0.5858 0.02635 0.01466 -0.0066 1.0000 0.1211
-5.500 -0.5763 0.02493 0.01347 -0.0042 1.0000 0.1481
-5.250 -0.5711 0.02314 0.01221 -0.0013 1.0000 0.2090
-5.000 -0.5734 0.02109 0.01152 0.0030 1.0000 0.3808
-4.750 -0.5653 0.02076 0.01182 0.0076 1.0000 0.5401
-4.500 -0.5530 0.02090 0.01205 0.0116 1.0000 0.6071
-4.250 -0.5398 0.02118 0.01232 0.0155 1.0000 0.6553
-4.000 -0.5274 0.02175 0.01290 0.0202 1.0000 0.7022
-3.750 -0.5113 0.02249 0.01361 0.0247 1.0000 0.7408
-3.500 -0.4948 0.02281 0.01383 0.0281 1.0000 0.7678
-3.250 -0.4752 0.02286 0.01373 0.0300 1.0000 0.7847
-3.000 -0.4570 0.02274 0.01347 0.0317 1.0000 0.7991
-2.750 -0.4392 0.02257 0.01314 0.0331 1.0000 0.8128
-2.500 -0.4210 0.02242 0.01286 0.0344 1.0000 0.8257
-2.250 -0.3838 0.02243 0.01269 0.0321 0.9940 0.8355
-2.000 -0.3426 0.02241 0.01247 0.0287 0.9850 0.8456
-1.750 -0.3029 0.02236 0.01226 0.0256 0.9754 0.8560
-1.250 -0.2194 0.02235 0.01200 0.0188 0.9578 0.8740
-1.000 -0.1748 0.02238 0.01194 0.0150 0.9498 0.8823
-0.750 -0.1330 0.02238 0.01186 0.0116 0.9409 0.8912
-0.500 -0.0869 0.02238 0.01181 0.0074 0.9336 0.8999
-0.250 -0.0440 0.02239 0.01179 0.0038 0.9247 0.9079
0.000 0.0000 0.02237 0.01175 0.0000 0.9173 0.9173
0.250 0.0440 0.02239 0.01179 -0.0038 0.9079 0.9247
0.500 0.0869 0.02238 0.01181 -0.0074 0.8999 0.9336
0.750 0.1330 0.02237 0.01186 -0.0116 0.8912 0.9409
1.000 0.1748 0.02238 0.01194 -0.0150 0.8824 0.9498
1.250 0.2194 0.02235 0.01200 -0.0188 0.8740 0.9579
1.500 0.2601 0.02238 0.01216 -0.0221 0.8642 0.9668
1.750 0.3030 0.02235 0.01226 -0.0256 0.8560 0.9754
2.000 0.3426 0.02240 0.01247 -0.0287 0.8456 0.9850
2.250 0.3838 0.02243 0.01269 -0.0321 0.8355 0.9940
2.500 0.4210 0.02242 0.01285 -0.0344 0.8257 1.0000
2.750 0.4391 0.02257 0.01314 -0.0331 0.8128 1.0000
3.000 0.4569 0.02274 0.01344 -0.0317 0.7991 1.0000
3.250 0.4751 0.02286 0.01373 -0.0300 0.7846 1.0000
3.500 0.4947 0.02281 0.01383 -0.0281 0.7678 1.0000
3.750 0.5113 0.02249 0.01361 -0.0247 0.7408 1.0000
4.000 0.5273 0.02175 0.01289 -0.0202 0.7022 1.0000
4.250 0.5398 0.02118 0.01232 -0.0155 0.6553 1.0000
4.500 0.5530 0.02090 0.01205 -0.0116 0.6071 1.0000
4.750 0.5653 0.02076 0.01182 -0.0076 0.5401 1.0000
5.000 0.5734 0.02109 0.01152 -0.0030 0.3807 1.0000
5.250 0.5711 0.02314 0.01220 0.0013 0.2090 1.0000
5.500 0.5763 0.02493 0.01346 0.0042 0.1481 1.0000
5.750 0.5858 0.02635 0.01466 0.0066 0.1211 1.0000
6.000 0.5979 0.02764 0.01587 0.0089 0.1057 1.0000
6.250 0.6123 0.02886 0.01707 0.0108 0.0936 1.0000
6.500 0.6286 0.03021 0.01833 0.0124 0.0858 1.0000
7.000 0.6732 0.03286 0.02108 0.0144 0.0718 1.0000
7.250 0.7013 0.03445 0.02295 0.0149 0.0677 1.0000
7.500 0.7266 0.03617 0.02483 0.0155 0.0637 1.0000
7.750 0.7492 0.03811 0.02673 0.0159 0.0600 1.0000
8.000 0.7701 0.04025 0.02930 0.0169 0.0573 1.0000
8.250 0.7894 0.04278 0.03223 0.0180 0.0558 1.0000
8.500 0.8052 0.04552 0.03537 0.0193 0.0546 1.0000
8.750 0.8174 0.04843 0.03867 0.0208 0.0537 1.0000
9.000 0.8263 0.05132 0.04191 0.0223 0.0525 1.0000
9.250 0.8336 0.05410 0.04496 0.0238 0.0510 1.0000
9.500 0.8415 0.05674 0.04775 0.0249 0.0495 1.0000
9.750 0.8460 0.05987 0.05105 0.0260 0.0484 1.0000
10.000 0.8426 0.06346 0.05488 0.0276 0.0479 1.0000
10.250 0.8338 0.06709 0.05881 0.0292 0.0478 1.0000
10.500 0.8212 0.07069 0.06264 0.0307 0.0478 1.0000
10.750 0.8058 0.07448 0.06661 0.0316 0.0479 1.0000
11.000 0.7895 0.07872 0.07100 0.0313 0.0480 1.0000
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