NACA M7 AIRFOIL (m7-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA M7 AIRFOIL (m7-il) Reynolds number: 100,000 Max Cl/Cd: 54.08 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m7-il-100000-n5.txt Download as CSV file: xf-m7-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M7 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4499 0.10132 0.09734 0.0217 0.8492 0.0211
-7.000 -0.4444 0.09837 0.09434 0.0200 0.8343 0.0216
-6.750 -0.4360 0.09522 0.09114 0.0178 0.8217 0.0221
-6.500 -0.4260 0.09201 0.08787 0.0156 0.8104 0.0227
-6.250 -0.4138 0.08872 0.08450 0.0130 0.7993 0.0234
-6.000 -0.4000 0.08544 0.08115 0.0104 0.7894 0.0242
-5.750 -0.3844 0.08223 0.07785 0.0077 0.7805 0.0251
-5.500 -0.3640 0.07919 0.07472 0.0041 0.7708 0.0261
-5.250 -0.3382 0.07678 0.07213 -0.0002 0.7622 0.0268
-5.000 -0.3111 0.07438 0.06954 -0.0039 0.7536 0.0271
-4.750 -0.2940 0.07016 0.06527 -0.0051 0.7457 0.0275
-4.500 -0.2874 0.06556 0.06069 -0.0038 0.7384 0.0293
-4.250 -0.2668 0.06252 0.05754 -0.0051 0.7301 0.0321
-4.000 -0.2255 0.06183 0.05644 -0.0091 0.7229 0.0363
-3.500 -0.1941 0.05374 0.04827 -0.0093 0.7085 0.0403
-3.250 -0.1626 0.05189 0.04618 -0.0109 0.7006 0.0458
-3.000 -0.1303 0.04982 0.04377 -0.0120 0.6942 0.0481
-2.750 -0.1146 0.04578 0.03975 -0.0120 0.6869 0.0509
-2.500 -0.0895 0.04345 0.03721 -0.0122 0.6803 0.0563
-2.250 -0.0565 0.04164 0.03503 -0.0129 0.6735 0.0625
-2.000 -0.0354 0.03872 0.03205 -0.0128 0.6668 0.0671
-1.750 -0.0004 0.03798 0.03079 -0.0128 0.6605 0.0756
-1.500 0.0230 0.03471 0.02745 -0.0128 0.6536 0.0773
-1.250 0.0499 0.03255 0.02503 -0.0124 0.6482 0.0788
-1.000 0.0865 0.02931 0.02130 -0.0113 0.6416 0.0337
-0.750 0.1157 0.02720 0.01885 -0.0107 0.6358 0.0307
-0.500 0.1471 0.02519 0.01636 -0.0100 0.6296 0.0284
-0.250 0.1772 0.02379 0.01455 -0.0093 0.6232 0.0269
0.000 0.2058 0.02221 0.01266 -0.0089 0.6179 0.0259
0.250 0.2356 0.02086 0.01105 -0.0086 0.6108 0.0253
0.500 0.2644 0.01969 0.00959 -0.0081 0.6054 0.0252
0.750 0.2936 0.01874 0.00847 -0.0079 0.5987 0.0257
1.000 0.3221 0.01793 0.00754 -0.0076 0.5927 0.0288
1.250 0.3513 0.01742 0.00685 -0.0075 0.5867 0.0314
1.500 0.3789 0.01713 0.00638 -0.0072 0.5801 0.0354
1.750 0.4052 0.01687 0.00603 -0.0065 0.5751 0.0563
2.250 0.5109 0.01512 0.00593 -0.0171 0.5608 1.0000
2.500 0.5374 0.01529 0.00599 -0.0170 0.5538 1.0000
2.750 0.5632 0.01544 0.00600 -0.0166 0.5480 1.0000
3.000 0.5892 0.01561 0.00608 -0.0163 0.5420 1.0000
3.250 0.6152 0.01579 0.00621 -0.0161 0.5355 1.0000
3.500 0.6407 0.01589 0.00624 -0.0156 0.5271 1.0000
3.750 0.6657 0.01590 0.00613 -0.0150 0.5162 1.0000
4.000 0.6912 0.01593 0.00611 -0.0145 0.5024 1.0000
4.250 0.7169 0.01602 0.00623 -0.0143 0.4903 1.0000
4.500 0.7426 0.01620 0.00641 -0.0140 0.4826 1.0000
4.750 0.7683 0.01638 0.00662 -0.0137 0.4749 1.0000
5.000 0.7940 0.01658 0.00692 -0.0135 0.4672 1.0000
5.250 0.8195 0.01677 0.00716 -0.0132 0.4593 1.0000
5.500 0.8450 0.01693 0.00740 -0.0129 0.4471 1.0000
5.750 0.8704 0.01708 0.00762 -0.0126 0.4334 1.0000
6.000 0.8957 0.01729 0.00797 -0.0123 0.4225 1.0000
6.250 0.9210 0.01750 0.00829 -0.0121 0.4096 1.0000
6.500 0.9459 0.01771 0.00859 -0.0118 0.3889 1.0000
6.750 0.9705 0.01799 0.00897 -0.0115 0.3630 1.0000
7.000 0.9946 0.01839 0.00939 -0.0113 0.3284 1.0000
7.250 1.0171 0.01911 0.00995 -0.0111 0.2714 1.0000
7.500 1.0316 0.02144 0.01145 -0.0114 0.1403 1.0000
7.750 1.0453 0.02370 0.01330 -0.0114 0.0823 1.0000
8.000 1.0638 0.02488 0.01457 -0.0109 0.0736 1.0000
8.250 1.0809 0.02613 0.01596 -0.0104 0.0695 1.0000
8.500 1.0978 0.02730 0.01733 -0.0098 0.0672 1.0000
8.750 1.1133 0.02851 0.01877 -0.0092 0.0653 1.0000
9.000 1.1268 0.02984 0.02033 -0.0084 0.0636 1.0000
9.250 1.1381 0.03129 0.02204 -0.0075 0.0621 1.0000
9.500 1.1472 0.03285 0.02380 -0.0065 0.0607 1.0000
9.750 1.1540 0.03456 0.02569 -0.0055 0.0595 1.0000
10.000 1.1580 0.03634 0.02761 -0.0041 0.0584 1.0000
10.250 1.1607 0.03834 0.02966 -0.0028 0.0558 1.0000
10.500 1.1662 0.04025 0.03180 -0.0026 0.0497 1.0000
10.750 1.1656 0.04281 0.03437 -0.0026 0.0437 1.0000
11.000 1.1703 0.04500 0.03680 -0.0024 0.0390 1.0000
11.250 1.1701 0.04774 0.03964 -0.0025 0.0341 1.0000
11.500 1.1734 0.05031 0.04254 -0.0026 0.0273 1.0000
11.750 1.1725 0.05337 0.04574 -0.0029 0.0223 1.0000
12.000 1.1757 0.05591 0.04848 -0.0020 0.0178 1.0000
12.250 1.1771 0.05879 0.05159 -0.0024 0.0149 1.0000
12.500 1.1757 0.06207 0.05498 -0.0032 0.0133 1.0000
12.750 1.1711 0.06573 0.05870 -0.0033 0.0123 1.0000
13.000 1.1694 0.06909 0.06227 -0.0028 0.0117 1.0000
13.250 1.1666 0.07276 0.06616 -0.0026 0.0112 1.0000
13.500 1.1619 0.07684 0.07047 -0.0029 0.0108 1.0000
13.750 1.1551 0.08135 0.07520 -0.0036 0.0106 1.0000
14.000 1.1465 0.08633 0.08042 -0.0049 0.0103 1.0000
14.250 1.1363 0.09180 0.08611 -0.0067 0.0102 1.0000
14.500 1.1243 0.09780 0.09232 -0.0091 0.0101 1.0000
14.750 1.1109 0.10439 0.09911 -0.0120 0.0101 1.0000
15.000 1.0957 0.11164 0.10657 -0.0155 0.0101 1.0000
15.250 1.0789 0.11964 0.11476 -0.0197 0.0103 1.0000
15.500 1.0613 0.12840 0.12367 -0.0244 0.0105 1.0000
15.750 1.0436 0.13777 0.13317 -0.0297 0.0108 1.0000
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Polar data table (+)
Polar graphs
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