NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 642-015A AIRFOIL (n64015a-il) Reynolds number: 500,000 Max Cl/Cd: 52.73 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64015a-il-500000-n5.txt Download as CSV file: xf-n64015a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015A 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
------ -------- --------- --------- -------- -------- --------
-19.250 -1.0228 0.13214 0.12903 0.0032 1.0000 0.0123
-19.000 -1.0493 0.12220 0.11890 -0.0025 1.0000 0.0123
-18.750 -1.0703 0.11382 0.11037 -0.0071 1.0000 0.0123
-18.500 -1.0882 0.10632 0.10272 -0.0111 1.0000 0.0124
-18.250 -1.1034 0.09953 0.09578 -0.0147 1.0000 0.0124
-18.000 -1.1167 0.09330 0.08942 -0.0178 1.0000 0.0124
-17.750 -1.1282 0.08760 0.08359 -0.0205 1.0000 0.0125
-17.500 -1.1378 0.08238 0.07824 -0.0229 1.0000 0.0126
-17.250 -1.1460 0.07754 0.07327 -0.0249 1.0000 0.0126
-17.000 -1.1526 0.07310 0.06871 -0.0267 1.0000 0.0127
-16.750 -1.1579 0.06899 0.06448 -0.0282 1.0000 0.0128
-16.500 -1.1620 0.06515 0.06052 -0.0294 1.0000 0.0129
-16.250 -1.1648 0.06161 0.05687 -0.0304 1.0000 0.0130
-16.000 -1.1664 0.05833 0.05348 -0.0312 1.0000 0.0131
-15.750 -1.1668 0.05530 0.05034 -0.0319 1.0000 0.0132
-15.500 -1.1661 0.05248 0.04741 -0.0323 1.0000 0.0134
-15.250 -1.1647 0.04984 0.04466 -0.0326 1.0000 0.0135
-15.000 -1.1624 0.04738 0.04209 -0.0327 1.0000 0.0137
-14.750 -1.1592 0.04505 0.03964 -0.0326 1.0000 0.0138
-14.500 -1.1551 0.04286 0.03734 -0.0325 1.0000 0.0140
-14.250 -1.1503 0.04079 0.03517 -0.0322 1.0000 0.0141
-14.000 -1.1444 0.03884 0.03311 -0.0318 1.0000 0.0143
-13.750 -1.1377 0.03702 0.03119 -0.0314 1.0000 0.0144
-13.500 -1.1301 0.03531 0.02939 -0.0309 1.0000 0.0145
-13.250 -1.1215 0.03371 0.02769 -0.0303 1.0000 0.0147
-13.000 -1.1121 0.03222 0.02610 -0.0297 1.0000 0.0148
-12.750 -1.1059 0.03049 0.02430 -0.0288 1.0000 0.0150
-12.500 -1.0976 0.02897 0.02273 -0.0279 1.0000 0.0152
-12.250 -1.0876 0.02764 0.02134 -0.0271 1.0000 0.0155
-12.000 -1.0763 0.02645 0.02010 -0.0262 1.0000 0.0157
-11.750 -1.0641 0.02535 0.01895 -0.0253 1.0000 0.0160
-11.500 -1.0513 0.02435 0.01789 -0.0243 1.0000 0.0163
-11.250 -1.0379 0.02342 0.01690 -0.0233 1.0000 0.0166
-11.000 -1.0241 0.02255 0.01598 -0.0221 1.0000 0.0170
-10.750 -1.0102 0.02173 0.01511 -0.0209 1.0000 0.0174
-10.500 -0.9961 0.02096 0.01428 -0.0196 1.0000 0.0178
-10.250 -0.9821 0.02025 0.01351 -0.0181 1.0000 0.0181
-10.000 -0.9688 0.01956 0.01276 -0.0163 1.0000 0.0185
-9.750 -0.9575 0.01885 0.01203 -0.0141 1.0000 0.0190
-9.500 -0.9456 0.01829 0.01146 -0.0118 1.0000 0.0195
-9.250 -0.9323 0.01780 0.01094 -0.0097 1.0000 0.0201
-9.000 -0.9059 0.01723 0.01034 -0.0102 0.9900 0.0209
-8.750 -0.8768 0.01667 0.00973 -0.0113 0.9765 0.0219
-8.500 -0.8481 0.01612 0.00913 -0.0122 0.9617 0.0230
-8.250 -0.8212 0.01558 0.00858 -0.0126 0.9445 0.0245
-8.000 -0.7971 0.01516 0.00810 -0.0123 0.9251 0.0262
-7.750 -0.7747 0.01481 0.00766 -0.0115 0.9058 0.0279
-7.500 -0.7535 0.01442 0.00723 -0.0105 0.8877 0.0305
-7.250 -0.7312 0.01411 0.00685 -0.0097 0.8717 0.0332
-7.000 -0.7090 0.01376 0.00646 -0.0089 0.8571 0.0369
-6.750 -0.6859 0.01347 0.00611 -0.0082 0.8440 0.0411
-6.500 -0.6628 0.01316 0.00577 -0.0075 0.8318 0.0468
-6.250 -0.6392 0.01285 0.00544 -0.0070 0.8205 0.0539
-6.000 -0.6155 0.01254 0.00513 -0.0064 0.8102 0.0633
-5.750 -0.5918 0.01222 0.00482 -0.0059 0.8003 0.0760
-5.500 -0.5681 0.01187 0.00451 -0.0054 0.7913 0.0939
-5.250 -0.5454 0.01145 0.00418 -0.0048 0.7823 0.1231
-5.000 -0.5232 0.01093 0.00384 -0.0041 0.7737 0.1659
-4.750 -0.5020 0.01035 0.00348 -0.0033 0.7655 0.2232
-4.500 -0.4809 0.00971 0.00311 -0.0024 0.7578 0.2909
-4.250 -0.4611 0.00902 0.00275 -0.0013 0.7503 0.3728
-4.000 -0.4389 0.00858 0.00256 -0.0005 0.7429 0.4431
-3.750 -0.4138 0.00837 0.00244 -0.0001 0.7353 0.4801
-3.500 -0.3875 0.00825 0.00235 0.0001 0.7282 0.5043
-3.250 -0.3605 0.00817 0.00226 0.0002 0.7209 0.5194
-2.750 -0.3072 0.00800 0.00215 0.0006 0.7077 0.5593
-2.500 -0.2800 0.00796 0.00210 0.0007 0.7010 0.5735
-2.250 -0.2525 0.00792 0.00205 0.0008 0.6944 0.5858
-2.000 -0.2251 0.00788 0.00201 0.0008 0.6874 0.5952
-1.750 -0.1970 0.00787 0.00195 0.0007 0.6811 0.6021
-1.500 -0.1689 0.00783 0.00191 0.0006 0.6747 0.6072
-1.250 -0.1409 0.00782 0.00187 0.0006 0.6687 0.6125
-1.000 -0.1125 0.00781 0.00184 0.0004 0.6629 0.6178
-0.750 -0.0845 0.00779 0.00181 0.0003 0.6567 0.6229
-0.250 -0.0280 0.00779 0.00178 0.0001 0.6447 0.6339
0.000 0.0000 0.00778 0.00178 0.0000 0.6390 0.6390
0.250 0.0281 0.00779 0.00178 -0.0001 0.6339 0.6447
0.750 0.0845 0.00779 0.00181 -0.0003 0.6229 0.6567
1.000 0.1125 0.00781 0.00184 -0.0004 0.6178 0.6629
1.250 0.1409 0.00782 0.00187 -0.0006 0.6125 0.6687
1.500 0.1690 0.00783 0.00191 -0.0006 0.6072 0.6747
1.750 0.1970 0.00787 0.00195 -0.0007 0.6021 0.6811
2.000 0.2251 0.00788 0.00201 -0.0008 0.5952 0.6874
2.250 0.2525 0.00792 0.00205 -0.0008 0.5858 0.6944
2.500 0.2801 0.00796 0.00210 -0.0007 0.5736 0.7010
2.750 0.3072 0.00800 0.00215 -0.0006 0.5594 0.7077
3.250 0.3605 0.00817 0.00226 -0.0002 0.5193 0.7209
3.500 0.3876 0.00825 0.00235 -0.0001 0.5040 0.7282
3.750 0.4139 0.00838 0.00244 0.0001 0.4798 0.7352
4.000 0.4389 0.00858 0.00256 0.0005 0.4432 0.7429
4.250 0.4612 0.00903 0.00275 0.0013 0.3724 0.7503
4.500 0.4810 0.00972 0.00311 0.0024 0.2906 0.7579
4.750 0.5021 0.01035 0.00348 0.0032 0.2230 0.7655
5.000 0.5233 0.01094 0.00384 0.0041 0.1656 0.7737
5.250 0.5455 0.01145 0.00418 0.0047 0.1230 0.7824
5.500 0.5682 0.01187 0.00451 0.0054 0.0938 0.7914
5.750 0.5920 0.01222 0.00482 0.0059 0.0759 0.8003
6.000 0.6157 0.01254 0.00513 0.0064 0.0633 0.8102
6.250 0.6394 0.01285 0.00544 0.0069 0.0538 0.8205
6.500 0.6630 0.01316 0.00577 0.0075 0.0468 0.8318
6.750 0.6861 0.01348 0.00611 0.0081 0.0410 0.8440
7.000 0.7093 0.01376 0.00646 0.0088 0.0369 0.8570
7.250 0.7315 0.01411 0.00685 0.0096 0.0332 0.8716
7.500 0.7538 0.01442 0.00723 0.0104 0.0304 0.8876
7.750 0.7750 0.01481 0.00766 0.0114 0.0279 0.9057
8.000 0.7974 0.01516 0.00810 0.0122 0.0262 0.9250
8.250 0.8215 0.01558 0.00858 0.0125 0.0245 0.9444
8.500 0.8484 0.01612 0.00913 0.0121 0.0230 0.9617
8.750 0.8771 0.01667 0.00973 0.0112 0.0219 0.9766
9.000 0.9061 0.01723 0.01034 0.0102 0.0209 0.9900
9.250 0.9324 0.01780 0.01094 0.0096 0.0201 1.0000
9.500 0.9459 0.01829 0.01146 0.0118 0.0195 1.0000
9.750 0.9579 0.01885 0.01203 0.0141 0.0190 1.0000
10.000 0.9692 0.01955 0.01276 0.0163 0.0185 1.0000
10.250 0.9825 0.02025 0.01351 0.0180 0.0181 1.0000
10.500 0.9967 0.02096 0.01428 0.0195 0.0178 1.0000
10.750 1.0108 0.02173 0.01510 0.0208 0.0174 1.0000
11.000 1.0248 0.02255 0.01598 0.0220 0.0170 1.0000
11.250 1.0387 0.02341 0.01690 0.0231 0.0166 1.0000
11.500 1.0521 0.02434 0.01789 0.0242 0.0163 1.0000
11.750 1.0651 0.02534 0.01894 0.0251 0.0160 1.0000
12.000 1.0773 0.02644 0.02009 0.0260 0.0157 1.0000
12.250 1.0888 0.02763 0.02133 0.0269 0.0155 1.0000
12.500 1.0988 0.02897 0.02272 0.0277 0.0152 1.0000
12.750 1.1072 0.03048 0.02429 0.0286 0.0150 1.0000
13.000 1.1135 0.03221 0.02609 0.0295 0.0148 1.0000
13.250 1.1230 0.03369 0.02767 0.0301 0.0147 1.0000
13.500 1.1317 0.03529 0.02936 0.0306 0.0145 1.0000
13.750 1.1393 0.03700 0.03117 0.0311 0.0144 1.0000
14.000 1.1462 0.03882 0.03309 0.0316 0.0143 1.0000
14.250 1.1521 0.04076 0.03514 0.0319 0.0141 1.0000
14.500 1.1570 0.04283 0.03732 0.0322 0.0140 1.0000
14.750 1.1611 0.04502 0.03962 0.0323 0.0138 1.0000
15.000 1.1645 0.04734 0.04205 0.0323 0.0137 1.0000
15.250 1.1668 0.04981 0.04463 0.0322 0.0135 1.0000
15.500 1.1682 0.05245 0.04738 0.0320 0.0134 1.0000
15.750 1.1690 0.05526 0.05030 0.0315 0.0132 1.0000
16.000 1.1687 0.05830 0.05344 0.0309 0.0131 1.0000
16.250 1.1671 0.06157 0.05682 0.0301 0.0130 1.0000
16.500 1.1644 0.06510 0.06047 0.0291 0.0129 1.0000
16.750 1.1605 0.06892 0.06441 0.0278 0.0128 1.0000
17.000 1.1551 0.07305 0.06866 0.0263 0.0127 1.0000
17.250 1.1485 0.07749 0.07322 0.0246 0.0126 1.0000
17.500 1.1404 0.08233 0.07818 0.0225 0.0125 1.0000
17.750 1.1309 0.08755 0.08353 0.0201 0.0125 1.0000
18.000 1.1193 0.09326 0.08937 0.0174 0.0124 1.0000
18.250 1.1060 0.09949 0.09574 0.0143 0.0124 1.0000
18.500 1.0909 0.10629 0.10269 0.0107 0.0124 1.0000
18.750 1.0727 0.11386 0.11040 0.0067 0.0123 1.0000
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