NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-015A AIRFOIL (n63015a-il) Reynolds number: 100,000 Max Cl/Cd: 44.44 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63015a-il-100000.txt Download as CSV file: xf-n63015a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-015A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7813 0.10155 0.09618 -0.0287 1.0000 0.0742
-13.250 -0.7859 0.09557 0.09019 -0.0302 1.0000 0.0733
-13.000 -0.8050 0.08853 0.08310 -0.0333 1.0000 0.0722
-12.750 -0.8349 0.08114 0.07558 -0.0367 1.0000 0.0708
-12.500 -0.8679 0.07446 0.06872 -0.0392 1.0000 0.0695
-12.250 -0.9015 0.06864 0.06265 -0.0401 1.0000 0.0682
-12.000 -0.9356 0.06360 0.05730 -0.0392 1.0000 0.0669
-11.750 -0.9741 0.05937 0.05263 -0.0358 1.0000 0.0655
-11.500 -0.9942 0.05616 0.04905 -0.0321 1.0000 0.0651
-11.250 -0.9958 0.05307 0.04571 -0.0300 1.0000 0.0654
-11.000 -0.9952 0.05002 0.04236 -0.0278 1.0000 0.0657
-10.750 -0.9909 0.04704 0.03907 -0.0257 1.0000 0.0659
-10.500 -0.9808 0.04430 0.03608 -0.0241 1.0000 0.0665
-10.250 -0.9675 0.04182 0.03334 -0.0226 1.0000 0.0675
-10.000 -0.9521 0.03956 0.03085 -0.0213 1.0000 0.0690
-9.750 -0.9369 0.03763 0.02866 -0.0198 1.0000 0.0715
-9.500 -0.9224 0.03600 0.02667 -0.0179 1.0000 0.0740
-9.250 -0.8944 0.03338 0.02412 -0.0184 1.0000 0.0775
-9.000 -0.8710 0.03172 0.02240 -0.0178 1.0000 0.0815
-8.500 -0.8271 0.02862 0.01931 -0.0163 1.0000 0.0941
-8.250 -0.8069 0.02713 0.01784 -0.0152 1.0000 0.1025
-8.000 -0.7916 0.02596 0.01669 -0.0133 1.0000 0.1136
-7.750 -0.7800 0.02470 0.01559 -0.0110 1.0000 0.1275
-7.500 -0.7740 0.02342 0.01456 -0.0077 1.0000 0.1446
-7.250 -0.7715 0.02222 0.01359 -0.0039 1.0000 0.1687
-7.000 -0.7740 0.02090 0.01265 0.0007 1.0000 0.2031
-6.750 -0.7815 0.01946 0.01175 0.0060 1.0000 0.2593
-6.500 -0.7896 0.01817 0.01119 0.0115 1.0000 0.3563
-6.250 -0.7877 0.01772 0.01118 0.0158 1.0000 0.4439
-6.000 -0.7786 0.01773 0.01126 0.0191 1.0000 0.4960
-5.750 -0.7660 0.01792 0.01148 0.0219 1.0000 0.5326
-5.500 -0.7518 0.01819 0.01171 0.0243 1.0000 0.5625
-5.250 -0.7351 0.01859 0.01212 0.0265 1.0000 0.5867
-5.000 -0.7192 0.01888 0.01234 0.0285 1.0000 0.6094
-4.750 -0.6984 0.01930 0.01275 0.0300 0.9992 0.6281
-4.500 -0.6556 0.01997 0.01337 0.0275 0.9913 0.6483
-4.250 -0.6125 0.02058 0.01392 0.0249 0.9835 0.6674
-4.000 -0.5742 0.02111 0.01439 0.0234 0.9745 0.6852
-3.750 -0.5337 0.02165 0.01488 0.0215 0.9668 0.7020
-3.500 -0.4940 0.02205 0.01522 0.0197 0.9585 0.7159
-3.250 -0.4567 0.02224 0.01532 0.0180 0.9502 0.7287
-3.000 -0.4169 0.02227 0.01525 0.0155 0.9423 0.7416
-2.750 -0.3783 0.02250 0.01544 0.0138 0.9344 0.7503
-2.500 -0.3378 0.02243 0.01528 0.0112 0.9268 0.7604
-2.250 -0.2979 0.02246 0.01526 0.0088 0.9196 0.7694
-2.000 -0.2610 0.02238 0.01512 0.0070 0.9113 0.7780
-1.750 -0.2224 0.02232 0.01501 0.0049 0.9043 0.7869
-1.500 -0.1900 0.02227 0.01492 0.0040 0.8951 0.7949
-1.250 -0.1528 0.02219 0.01479 0.0022 0.8882 0.8036
-1.000 -0.1237 0.02216 0.01475 0.0020 0.8786 0.8116
-0.750 -0.0893 0.02208 0.01465 0.0009 0.8714 0.8204
-0.500 -0.0609 0.02208 0.01464 0.0008 0.8618 0.8283
-0.250 -0.0294 0.02203 0.01457 0.0002 0.8543 0.8373
0.000 0.0000 0.02205 0.01459 0.0000 0.8450 0.8450
0.250 0.0294 0.02203 0.01457 -0.0002 0.8373 0.8543
0.500 0.0609 0.02208 0.01464 -0.0008 0.8283 0.8619
0.750 0.0893 0.02208 0.01464 -0.0009 0.8203 0.8714
1.000 0.1237 0.02216 0.01475 -0.0020 0.8116 0.8786
1.250 0.1527 0.02219 0.01479 -0.0022 0.8036 0.8883
1.500 0.1900 0.02227 0.01492 -0.0040 0.7949 0.8951
1.750 0.2223 0.02232 0.01501 -0.0049 0.7868 0.9043
2.000 0.2610 0.02238 0.01512 -0.0070 0.7780 0.9113
2.250 0.2979 0.02246 0.01526 -0.0088 0.7694 0.9196
2.500 0.3378 0.02242 0.01528 -0.0112 0.7604 0.9269
2.750 0.3783 0.02250 0.01544 -0.0138 0.7503 0.9344
3.000 0.4169 0.02226 0.01525 -0.0155 0.7416 0.9424
3.250 0.4566 0.02224 0.01532 -0.0180 0.7287 0.9503
3.500 0.4940 0.02204 0.01521 -0.0197 0.7160 0.9586
3.750 0.5336 0.02165 0.01488 -0.0215 0.7020 0.9669
4.000 0.5742 0.02111 0.01439 -0.0234 0.6853 0.9746
4.250 0.6125 0.02057 0.01391 -0.0249 0.6674 0.9835
4.500 0.6556 0.01996 0.01337 -0.0275 0.6483 0.9914
4.750 0.6984 0.01930 0.01275 -0.0300 0.6281 0.9992
5.000 0.7190 0.01888 0.01233 -0.0285 0.6095 1.0000
5.250 0.7349 0.01859 0.01212 -0.0265 0.5867 1.0000
5.500 0.7516 0.01818 0.01171 -0.0243 0.5625 1.0000
5.750 0.7658 0.01792 0.01148 -0.0218 0.5327 1.0000
6.000 0.7785 0.01773 0.01126 -0.0191 0.4962 1.0000
6.250 0.7875 0.01772 0.01118 -0.0158 0.4441 1.0000
6.500 0.7895 0.01816 0.01119 -0.0115 0.3566 1.0000
6.750 0.7814 0.01945 0.01174 -0.0060 0.2596 1.0000
7.000 0.7740 0.02090 0.01264 -0.0007 0.2031 1.0000
7.250 0.7715 0.02222 0.01359 0.0039 0.1688 1.0000
7.500 0.7740 0.02341 0.01456 0.0077 0.1446 1.0000
7.750 0.7800 0.02470 0.01559 0.0110 0.1275 1.0000
8.000 0.7917 0.02596 0.01669 0.0133 0.1136 1.0000
8.250 0.8070 0.02713 0.01784 0.0152 0.1025 1.0000
8.500 0.8272 0.02862 0.01931 0.0163 0.0941 1.0000
8.750 0.8521 0.03047 0.02090 0.0164 0.0864 1.0000
9.000 0.8712 0.03172 0.02240 0.0178 0.0815 1.0000
9.250 0.8946 0.03338 0.02412 0.0184 0.0775 1.0000
9.500 0.9226 0.03600 0.02667 0.0179 0.0740 1.0000
9.750 0.9370 0.03763 0.02867 0.0198 0.0715 1.0000
10.000 0.9523 0.03956 0.03086 0.0213 0.0690 1.0000
10.250 0.9677 0.04183 0.03335 0.0226 0.0675 1.0000
10.500 0.9810 0.04431 0.03609 0.0240 0.0665 1.0000
10.750 0.9911 0.04705 0.03908 0.0257 0.0659 1.0000
11.000 0.9955 0.05003 0.04238 0.0277 0.0657 1.0000
11.250 0.9958 0.05309 0.04574 0.0300 0.0654 1.0000
11.500 0.9930 0.05620 0.04911 0.0322 0.0652 1.0000
11.750 0.9734 0.05942 0.05270 0.0358 0.0656 1.0000
12.000 0.9359 0.06365 0.05736 0.0391 0.0669 1.0000
12.250 0.9017 0.06872 0.06274 0.0399 0.0682 1.0000
12.500 0.8683 0.07455 0.06881 0.0390 0.0695 1.0000
12.750 0.8354 0.08126 0.07571 0.0365 0.0708 1.0000
13.000 0.8059 0.08862 0.08319 0.0331 0.0722 1.0000
13.250 0.7870 0.09566 0.09028 0.0300 0.0733 1.0000
13.500 0.7829 0.10160 0.09624 0.0286 0.0742 1.0000
13.750 0.6421 0.15038 0.14509 -0.0033 0.1424 1.0000
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