NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-015A AIRFOIL (n63015a-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.82 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63015a-il-1000000.txt Download as CSV file: xf-n63015a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.1799 0.08928 0.08583 -0.0163 1.0000 0.0119
-18.000 -1.1959 0.08331 0.07972 -0.0187 1.0000 0.0120
-17.750 -1.2099 0.07787 0.07414 -0.0207 1.0000 0.0121
-17.500 -1.2207 0.07302 0.06918 -0.0223 1.0000 0.0121
-17.250 -1.2290 0.06860 0.06464 -0.0237 1.0000 0.0122
-17.000 -1.2354 0.06453 0.06048 -0.0249 1.0000 0.0123
-16.750 -1.2400 0.06080 0.05666 -0.0259 1.0000 0.0124
-16.500 -1.2430 0.05734 0.05311 -0.0268 1.0000 0.0125
-16.250 -1.2442 0.05416 0.04986 -0.0275 1.0000 0.0126
-16.000 -1.2442 0.05123 0.04686 -0.0280 1.0000 0.0127
-15.750 -1.2432 0.04850 0.04405 -0.0285 1.0000 0.0129
-15.500 -1.2408 0.04598 0.04145 -0.0287 1.0000 0.0130
-15.250 -1.2380 0.04358 0.03898 -0.0289 1.0000 0.0132
-15.000 -1.2345 0.04131 0.03663 -0.0289 1.0000 0.0133
-14.750 -1.2303 0.03913 0.03437 -0.0287 1.0000 0.0134
-14.500 -1.2254 0.03707 0.03223 -0.0285 1.0000 0.0136
-14.250 -1.2197 0.03514 0.03022 -0.0282 1.0000 0.0137
-14.000 -1.2130 0.03331 0.02832 -0.0278 1.0000 0.0139
-13.750 -1.2055 0.03162 0.02654 -0.0273 1.0000 0.0141
-13.500 -1.1969 0.03004 0.02489 -0.0267 1.0000 0.0142
-13.250 -1.1876 0.02857 0.02334 -0.0261 1.0000 0.0144
-13.000 -1.1771 0.02723 0.02193 -0.0254 1.0000 0.0145
-12.750 -1.1655 0.02602 0.02066 -0.0247 1.0000 0.0147
-12.500 -1.1528 0.02493 0.01950 -0.0239 1.0000 0.0148
-12.250 -1.1509 0.02308 0.01756 -0.0222 1.0000 0.0151
-12.000 -1.1435 0.02174 0.01617 -0.0207 1.0000 0.0154
-11.750 -1.1325 0.02072 0.01510 -0.0192 1.0000 0.0157
-11.500 -1.1194 0.01989 0.01422 -0.0179 1.0000 0.0160
-11.250 -1.1051 0.01917 0.01347 -0.0165 1.0000 0.0163
-11.000 -1.0901 0.01854 0.01281 -0.0150 1.0000 0.0167
-10.750 -1.0751 0.01796 0.01219 -0.0134 1.0000 0.0171
-10.500 -1.0603 0.01742 0.01161 -0.0116 1.0000 0.0175
-10.250 -1.0443 0.01692 0.01107 -0.0100 1.0000 0.0178
-10.000 -1.0264 0.01647 0.01058 -0.0086 1.0000 0.0181
-9.750 -1.0147 0.01570 0.00977 -0.0062 1.0000 0.0188
-9.500 -1.0000 0.01521 0.00926 -0.0041 1.0000 0.0195
-9.250 -0.9854 0.01483 0.00886 -0.0019 1.0000 0.0202
-9.000 -0.9656 0.01444 0.00846 -0.0008 0.9991 0.0210
-8.750 -0.9313 0.01402 0.00801 -0.0026 0.9955 0.0219
-8.500 -0.8996 0.01337 0.00736 -0.0041 0.9905 0.0241
-8.250 -0.8662 0.01295 0.00693 -0.0058 0.9842 0.0261
-8.000 -0.8359 0.01244 0.00644 -0.0068 0.9742 0.0296
-7.750 -0.8065 0.01202 0.00602 -0.0075 0.9613 0.0338
-7.500 -0.7805 0.01166 0.00564 -0.0074 0.9440 0.0387
-7.250 -0.7574 0.01132 0.00530 -0.0066 0.9242 0.0455
-7.000 -0.7349 0.01099 0.00496 -0.0057 0.9046 0.0552
-6.750 -0.7119 0.01066 0.00464 -0.0049 0.8861 0.0676
-6.500 -0.6884 0.01034 0.00434 -0.0043 0.8692 0.0819
-6.250 -0.6645 0.01005 0.00406 -0.0037 0.8541 0.0986
-6.000 -0.6411 0.00968 0.00376 -0.0031 0.8401 0.1233
-5.750 -0.6175 0.00928 0.00346 -0.0025 0.8273 0.1555
-5.500 -0.5944 0.00882 0.00316 -0.0019 0.8159 0.1965
-5.250 -0.5717 0.00834 0.00285 -0.0013 0.8053 0.2468
-5.000 -0.5499 0.00774 0.00253 -0.0005 0.7950 0.3148
-4.750 -0.5272 0.00724 0.00229 0.0002 0.7858 0.3821
-4.500 -0.5019 0.00698 0.00213 0.0006 0.7769 0.4216
-4.250 -0.4753 0.00682 0.00202 0.0007 0.7686 0.4467
-4.000 -0.4483 0.00671 0.00193 0.0008 0.7602 0.4674
-3.750 -0.4214 0.00658 0.00184 0.0010 0.7526 0.4890
-3.500 -0.3939 0.00650 0.00177 0.0010 0.7446 0.5059
-3.250 -0.3662 0.00644 0.00170 0.0010 0.7373 0.5184
-2.750 -0.3103 0.00635 0.00158 0.0009 0.7224 0.5406
-2.500 -0.2824 0.00628 0.00154 0.0009 0.7148 0.5533
-2.000 -0.2261 0.00622 0.00146 0.0007 0.7004 0.5764
-1.750 -0.1984 0.00619 0.00143 0.0007 0.6930 0.5865
-1.500 -0.1700 0.00617 0.00140 0.0006 0.6859 0.5962
-1.250 -0.1419 0.00614 0.00138 0.0006 0.6785 0.6057
-1.000 -0.1136 0.00613 0.00136 0.0005 0.6715 0.6136
-0.750 -0.0852 0.00611 0.00134 0.0004 0.6641 0.6213
-0.500 -0.0568 0.00612 0.00133 0.0002 0.6571 0.6282
-0.250 -0.0284 0.00610 0.00133 0.0001 0.6498 0.6356
0.000 0.0000 0.00613 0.00132 0.0000 0.6427 0.6427
0.250 0.0284 0.00610 0.00133 -0.0001 0.6356 0.6498
0.500 0.0568 0.00612 0.00133 -0.0002 0.6282 0.6571
0.750 0.0851 0.00611 0.00134 -0.0004 0.6213 0.6641
1.000 0.1135 0.00613 0.00136 -0.0005 0.6136 0.6715
1.250 0.1418 0.00614 0.00138 -0.0006 0.6057 0.6785
1.500 0.1699 0.00617 0.00140 -0.0006 0.5962 0.6859
1.750 0.1984 0.00619 0.00143 -0.0007 0.5866 0.6929
2.000 0.2261 0.00622 0.00146 -0.0007 0.5764 0.7004
2.500 0.2824 0.00628 0.00154 -0.0009 0.5533 0.7148
2.750 0.3103 0.00635 0.00158 -0.0009 0.5407 0.7224
3.250 0.3662 0.00644 0.00170 -0.0010 0.5184 0.7372
3.500 0.3940 0.00650 0.00177 -0.0010 0.5060 0.7446
3.750 0.4213 0.00658 0.00184 -0.0010 0.4889 0.7526
4.000 0.4483 0.00671 0.00193 -0.0008 0.4673 0.7602
4.250 0.4753 0.00682 0.00202 -0.0007 0.4466 0.7686
4.500 0.5020 0.00698 0.00213 -0.0006 0.4216 0.7769
4.750 0.5272 0.00724 0.00229 -0.0002 0.3820 0.7858
5.000 0.5499 0.00774 0.00253 0.0005 0.3148 0.7950
5.250 0.5717 0.00834 0.00286 0.0013 0.2465 0.8053
5.500 0.5944 0.00882 0.00316 0.0019 0.1963 0.8159
5.750 0.6176 0.00928 0.00346 0.0025 0.1554 0.8273
6.000 0.6411 0.00968 0.00376 0.0031 0.1232 0.8401
6.250 0.6646 0.01005 0.00406 0.0037 0.0988 0.8541
6.500 0.6885 0.01034 0.00434 0.0042 0.0818 0.8693
6.750 0.7120 0.01066 0.00464 0.0049 0.0675 0.8862
7.000 0.7349 0.01099 0.00496 0.0057 0.0552 0.9047
7.250 0.7575 0.01132 0.00530 0.0066 0.0455 0.9242
7.500 0.7806 0.01166 0.00565 0.0074 0.0387 0.9439
7.750 0.8066 0.01202 0.00602 0.0075 0.0337 0.9612
8.000 0.8361 0.01244 0.00644 0.0068 0.0296 0.9742
8.250 0.8665 0.01295 0.00693 0.0057 0.0261 0.9842
8.500 0.8998 0.01337 0.00736 0.0041 0.0241 0.9906
8.750 0.9315 0.01402 0.00801 0.0026 0.0219 0.9956
9.000 0.9657 0.01444 0.00846 0.0007 0.0210 0.9991
9.250 0.9853 0.01482 0.00886 0.0019 0.0202 1.0000
9.500 1.0001 0.01521 0.00926 0.0041 0.0195 1.0000
9.750 1.0148 0.01570 0.00977 0.0062 0.0188 1.0000
10.000 1.0265 0.01647 0.01058 0.0086 0.0181 1.0000
10.250 1.0445 0.01692 0.01106 0.0099 0.0178 1.0000
10.500 1.0606 0.01742 0.01161 0.0116 0.0175 1.0000
10.750 1.0755 0.01796 0.01219 0.0133 0.0171 1.0000
11.000 1.0907 0.01853 0.01280 0.0149 0.0167 1.0000
11.250 1.1057 0.01917 0.01347 0.0164 0.0163 1.0000
11.500 1.1201 0.01988 0.01422 0.0177 0.0160 1.0000
11.750 1.1333 0.02072 0.01510 0.0191 0.0157 1.0000
12.000 1.1443 0.02175 0.01617 0.0205 0.0154 1.0000
12.250 1.1519 0.02308 0.01756 0.0220 0.0151 1.0000
12.500 1.1539 0.02493 0.01951 0.0237 0.0148 1.0000
12.750 1.1667 0.02601 0.02065 0.0245 0.0146 1.0000
13.000 1.1784 0.02722 0.02193 0.0252 0.0145 1.0000
13.250 1.1889 0.02856 0.02333 0.0259 0.0144 1.0000
13.500 1.1985 0.03002 0.02486 0.0265 0.0142 1.0000
13.750 1.2070 0.03160 0.02652 0.0270 0.0140 1.0000
14.000 1.2146 0.03329 0.02830 0.0275 0.0139 1.0000
14.250 1.2214 0.03511 0.03019 0.0279 0.0137 1.0000
14.500 1.2273 0.03704 0.03220 0.0282 0.0136 1.0000
14.750 1.2322 0.03909 0.03433 0.0285 0.0134 1.0000
15.000 1.2364 0.04128 0.03660 0.0286 0.0133 1.0000
15.250 1.2401 0.04354 0.03893 0.0286 0.0132 1.0000
15.500 1.2430 0.04593 0.04140 0.0284 0.0130 1.0000
15.750 1.2452 0.04847 0.04402 0.0282 0.0129 1.0000
16.000 1.2465 0.05117 0.04680 0.0277 0.0127 1.0000
16.250 1.2465 0.05410 0.04980 0.0272 0.0126 1.0000
16.500 1.2453 0.05728 0.05305 0.0264 0.0125 1.0000
16.750 1.2424 0.06074 0.05660 0.0256 0.0124 1.0000
17.000 1.2376 0.06449 0.06044 0.0246 0.0123 1.0000
17.250 1.2315 0.06853 0.06458 0.0234 0.0122 1.0000
17.500 1.2227 0.07302 0.06918 0.0219 0.0121 1.0000
17.750 1.2114 0.07794 0.07422 0.0203 0.0120 1.0000
18.000 1.1976 0.08338 0.07979 0.0183 0.0120 1.0000
18.250 1.1806 0.08948 0.08605 0.0159 0.0119 1.0000
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