NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63012A AIRFOIL (n63012a-il) Reynolds number: 500,000 Max Cl/Cd: 54.25 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63012a-il-500000-n5.txt Download as CSV file: xf-n63012a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63012A AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0050 0.09854 0.09567 -0.0009 1.0000 0.0092
-15.750 -1.0336 0.08807 0.08503 -0.0071 1.0000 0.0092
-15.500 -1.0574 0.07935 0.07613 -0.0123 1.0000 0.0091
-15.250 -1.0766 0.07205 0.06865 -0.0166 1.0000 0.0092
-15.000 -1.0931 0.06575 0.06216 -0.0199 1.0000 0.0092
-14.750 -1.1057 0.06040 0.05663 -0.0225 1.0000 0.0092
-14.500 -1.1170 0.05554 0.05159 -0.0246 1.0000 0.0093
-14.250 -1.1307 0.05066 0.04652 -0.0262 1.0000 0.0094
-14.000 -1.1389 0.04674 0.04244 -0.0271 1.0000 0.0095
-13.750 -1.1423 0.04357 0.03914 -0.0276 1.0000 0.0096
-13.500 -1.1423 0.04097 0.03640 -0.0277 1.0000 0.0098
-13.250 -1.1397 0.03875 0.03407 -0.0275 1.0000 0.0099
-13.000 -1.1357 0.03677 0.03198 -0.0271 1.0000 0.0101
-12.750 -1.1305 0.03498 0.03008 -0.0265 1.0000 0.0102
-12.500 -1.1246 0.03332 0.02831 -0.0255 1.0000 0.0104
-12.250 -1.1179 0.03176 0.02662 -0.0244 1.0000 0.0106
-12.000 -1.1102 0.03030 0.02502 -0.0230 1.0000 0.0108
-11.750 -1.1014 0.02894 0.02354 -0.0215 1.0000 0.0110
-11.500 -1.0914 0.02769 0.02216 -0.0199 1.0000 0.0112
-11.250 -1.0801 0.02654 0.02088 -0.0182 1.0000 0.0114
-11.000 -1.0674 0.02546 0.01966 -0.0166 1.0000 0.0116
-10.750 -1.0522 0.02444 0.01851 -0.0153 1.0000 0.0119
-10.500 -1.0353 0.02355 0.01751 -0.0142 1.0000 0.0121
-10.250 -1.0172 0.02276 0.01661 -0.0131 1.0000 0.0123
-10.000 -1.0013 0.02165 0.01541 -0.0118 1.0000 0.0126
-9.750 -0.9848 0.02062 0.01432 -0.0106 1.0000 0.0130
-9.500 -0.9665 0.01980 0.01343 -0.0095 1.0000 0.0133
-9.250 -0.9472 0.01909 0.01266 -0.0084 1.0000 0.0136
-9.000 -0.9275 0.01841 0.01193 -0.0074 1.0000 0.0139
-8.750 -0.9075 0.01777 0.01124 -0.0064 1.0000 0.0142
-8.500 -0.8874 0.01716 0.01058 -0.0054 1.0000 0.0146
-8.250 -0.8672 0.01660 0.00996 -0.0043 1.0000 0.0151
-8.000 -0.8469 0.01608 0.00938 -0.0032 1.0000 0.0156
-7.750 -0.8268 0.01560 0.00885 -0.0020 1.0000 0.0161
-7.500 -0.8073 0.01513 0.00833 -0.0007 1.0000 0.0164
-7.250 -0.7856 0.01448 0.00765 0.0001 0.9981 0.0173
-7.000 -0.7539 0.01394 0.00708 -0.0012 0.9921 0.0182
-6.750 -0.7218 0.01348 0.00659 -0.0025 0.9852 0.0194
-6.500 -0.6904 0.01307 0.00613 -0.0036 0.9764 0.0208
-6.250 -0.6594 0.01263 0.00566 -0.0046 0.9664 0.0228
-6.000 -0.6285 0.01223 0.00526 -0.0056 0.9549 0.0259
-5.750 -0.5985 0.01189 0.00489 -0.0062 0.9417 0.0299
-5.500 -0.5705 0.01156 0.00456 -0.0065 0.9264 0.0358
-5.250 -0.5443 0.01125 0.00423 -0.0062 0.9100 0.0445
-5.000 -0.5189 0.01096 0.00394 -0.0058 0.8934 0.0555
-4.750 -0.4939 0.01067 0.00366 -0.0054 0.8777 0.0707
-4.500 -0.4693 0.01033 0.00338 -0.0049 0.8626 0.0955
-4.250 -0.4457 0.00986 0.00306 -0.0043 0.8485 0.1415
-4.000 -0.4232 0.00923 0.00272 -0.0037 0.8354 0.2176
-3.750 -0.4006 0.00862 0.00241 -0.0030 0.8230 0.3005
-3.500 -0.3773 0.00813 0.00218 -0.0024 0.8115 0.3769
-3.250 -0.3525 0.00781 0.00201 -0.0020 0.8004 0.4328
-3.000 -0.3271 0.00757 0.00190 -0.0016 0.7903 0.4789
-2.500 -0.2749 0.00727 0.00173 -0.0009 0.7708 0.5462
-2.250 -0.2482 0.00718 0.00167 -0.0007 0.7619 0.5709
-2.000 -0.2212 0.00711 0.00163 -0.0005 0.7526 0.5919
-1.750 -0.1940 0.00706 0.00158 -0.0003 0.7439 0.6092
-1.500 -0.1667 0.00702 0.00154 -0.0002 0.7351 0.6244
-1.250 -0.1390 0.00699 0.00151 -0.0001 0.7261 0.6364
-1.000 -0.1113 0.00698 0.00147 -0.0001 0.7176 0.6458
-0.750 -0.0834 0.00696 0.00145 -0.0001 0.7084 0.6551
-0.500 -0.0557 0.00695 0.00143 0.0000 0.6997 0.6637
-0.250 -0.0278 0.00695 0.00141 0.0000 0.6906 0.6730
0.000 0.0000 0.00694 0.00141 0.0000 0.6817 0.6816
0.250 0.0278 0.00695 0.00141 0.0000 0.6730 0.6906
0.500 0.0557 0.00695 0.00143 0.0000 0.6637 0.6997
0.750 0.0835 0.00696 0.00145 0.0001 0.6551 0.7084
1.000 0.1113 0.00698 0.00147 0.0001 0.6458 0.7176
1.250 0.1390 0.00699 0.00151 0.0001 0.6364 0.7262
1.500 0.1667 0.00702 0.00154 0.0002 0.6244 0.7351
1.750 0.1940 0.00706 0.00158 0.0003 0.6092 0.7439
2.000 0.2212 0.00711 0.00163 0.0005 0.5918 0.7526
2.250 0.2481 0.00718 0.00167 0.0007 0.5709 0.7619
2.500 0.2749 0.00727 0.00173 0.0009 0.5462 0.7708
3.000 0.3270 0.00758 0.00190 0.0016 0.4786 0.7904
3.250 0.3524 0.00781 0.00201 0.0020 0.4331 0.8005
3.500 0.3773 0.00813 0.00218 0.0024 0.3772 0.8115
3.750 0.4006 0.00862 0.00241 0.0030 0.3008 0.8231
4.000 0.4232 0.00923 0.00272 0.0037 0.2183 0.8354
4.250 0.4456 0.00986 0.00306 0.0043 0.1418 0.8485
4.500 0.4693 0.01033 0.00338 0.0049 0.0955 0.8627
4.750 0.4938 0.01067 0.00366 0.0054 0.0707 0.8777
5.000 0.5188 0.01096 0.00394 0.0059 0.0555 0.8935
5.250 0.5442 0.01125 0.00423 0.0063 0.0445 0.9101
5.500 0.5704 0.01156 0.00455 0.0065 0.0358 0.9264
5.750 0.5984 0.01189 0.00489 0.0063 0.0299 0.9417
6.000 0.6285 0.01223 0.00526 0.0056 0.0259 0.9549
6.250 0.6593 0.01263 0.00567 0.0046 0.0228 0.9664
6.500 0.6904 0.01307 0.00613 0.0036 0.0208 0.9764
6.750 0.7218 0.01348 0.00659 0.0025 0.0194 0.9851
7.000 0.7538 0.01394 0.00708 0.0012 0.0182 0.9921
7.250 0.7855 0.01448 0.00765 -0.0001 0.0172 0.9981
7.500 0.8073 0.01513 0.00833 0.0007 0.0164 1.0000
7.750 0.8268 0.01560 0.00885 0.0020 0.0161 1.0000
8.000 0.8469 0.01608 0.00938 0.0032 0.0156 1.0000
8.250 0.8672 0.01660 0.00996 0.0043 0.0151 1.0000
8.500 0.8874 0.01716 0.01057 0.0054 0.0146 1.0000
8.750 0.9075 0.01777 0.01124 0.0064 0.0142 1.0000
9.000 0.9275 0.01841 0.01193 0.0074 0.0139 1.0000
9.250 0.9472 0.01908 0.01266 0.0084 0.0136 1.0000
9.500 0.9665 0.01980 0.01343 0.0095 0.0133 1.0000
9.750 0.9849 0.02062 0.01432 0.0105 0.0130 1.0000
10.000 1.0013 0.02165 0.01541 0.0118 0.0126 1.0000
10.250 1.0172 0.02276 0.01662 0.0131 0.0123 1.0000
10.500 1.0354 0.02355 0.01751 0.0142 0.0121 1.0000
10.750 1.0523 0.02444 0.01851 0.0153 0.0119 1.0000
11.000 1.0675 0.02546 0.01966 0.0166 0.0116 1.0000
11.250 1.0802 0.02654 0.02087 0.0182 0.0114 1.0000
11.500 1.0915 0.02769 0.02216 0.0199 0.0112 1.0000
11.750 1.1016 0.02894 0.02354 0.0215 0.0110 1.0000
12.000 1.1104 0.03029 0.02502 0.0230 0.0108 1.0000
12.250 1.1182 0.03175 0.02661 0.0243 0.0106 1.0000
12.500 1.1249 0.03331 0.02829 0.0255 0.0104 1.0000
12.750 1.1309 0.03497 0.03007 0.0264 0.0102 1.0000
13.000 1.1362 0.03674 0.03195 0.0271 0.0101 1.0000
13.250 1.1404 0.03870 0.03402 0.0275 0.0099 1.0000
13.500 1.1428 0.04095 0.03638 0.0276 0.0098 1.0000
13.750 1.1430 0.04354 0.03911 0.0275 0.0096 1.0000
14.000 1.1395 0.04671 0.04242 0.0270 0.0095 1.0000
14.250 1.1313 0.05063 0.04650 0.0261 0.0094 1.0000
14.500 1.1177 0.05552 0.05157 0.0245 0.0093 1.0000
14.750 1.1065 0.06038 0.05661 0.0224 0.0092 1.0000
15.000 1.0940 0.06574 0.06216 0.0198 0.0092 1.0000
15.250 1.0776 0.07202 0.06862 0.0164 0.0092 1.0000
15.500 1.0580 0.07942 0.07620 0.0121 0.0091 1.0000
15.750 1.0347 0.08807 0.08503 0.0069 0.0092 1.0000
16.000 1.0060 0.09858 0.09572 0.0006 0.0092 1.0000
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