USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa5-il-1000000.txt Download as CSV file: xf-usa5-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 5 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3411 0.09987 0.09829 -0.0222 1.0000 0.0079
-8.500 -0.3394 0.09720 0.09564 -0.0227 1.0000 0.0080
-8.250 -0.3387 0.09460 0.09307 -0.0227 1.0000 0.0080
-6.500 -0.2633 0.06544 0.06395 -0.0506 0.9848 0.0085
-6.250 -0.2357 0.06146 0.05993 -0.0566 0.9827 0.0088
-6.000 -0.2135 0.05950 0.05795 -0.0591 0.9782 0.0102
-5.750 -0.1823 0.05483 0.05322 -0.0657 0.9740 0.0114
-5.500 -0.1414 0.05043 0.04873 -0.0729 0.9710 0.0126
-5.250 -0.1095 0.04583 0.04403 -0.0780 0.9655 0.0126
-4.500 -0.0700 0.01346 0.00965 -0.0804 0.9308 0.0087
-4.250 -0.0486 0.01157 0.00735 -0.0789 0.9210 0.0087
-4.000 -0.0246 0.01041 0.00594 -0.0779 0.9116 0.0095
-3.750 0.0008 0.00991 0.00533 -0.0772 0.9014 0.0104
-3.500 0.0266 0.00954 0.00485 -0.0765 0.8906 0.0116
-3.250 0.0519 0.00901 0.00417 -0.0757 0.8774 0.0122
-3.000 0.0774 0.00867 0.00368 -0.0750 0.8615 0.0126
-2.750 0.1005 0.00786 0.00266 -0.0737 0.8434 0.0151
-2.500 0.1258 0.00772 0.00244 -0.0729 0.8242 0.0176
-2.250 0.1506 0.00760 0.00219 -0.0720 0.8026 0.0192
-2.000 0.1741 0.00726 0.00171 -0.0709 0.7791 0.0248
-1.750 0.1988 0.00725 0.00159 -0.0701 0.7554 0.0289
-1.500 0.2223 0.00710 0.00134 -0.0689 0.7286 0.0388
-1.250 0.2462 0.00706 0.00120 -0.0680 0.7015 0.0485
-1.000 0.2701 0.00707 0.00117 -0.0670 0.6733 0.0703
-0.750 0.2950 0.00717 0.00119 -0.0663 0.6487 0.0838
-0.500 0.3204 0.00730 0.00123 -0.0657 0.6251 0.0910
-0.250 0.3453 0.00735 0.00119 -0.0650 0.6017 0.0959
0.000 0.3702 0.00744 0.00119 -0.0643 0.5758 0.1011
0.250 0.3949 0.00757 0.00118 -0.0636 0.5433 0.1044
0.500 0.4185 0.00773 0.00116 -0.0627 0.5003 0.1075
0.750 0.4416 0.00791 0.00116 -0.0618 0.4565 0.1117
1.000 0.4660 0.00804 0.00118 -0.0611 0.4295 0.1155
1.250 0.4911 0.00816 0.00122 -0.0605 0.4107 0.1204
1.500 0.5162 0.00821 0.00123 -0.0599 0.3965 0.1264
2.000 0.5672 0.00832 0.00130 -0.0589 0.3749 0.1404
2.250 0.5923 0.00832 0.00137 -0.0584 0.3668 0.1774
2.500 0.7282 0.00692 0.00175 -0.0842 0.3506 1.0000
2.750 0.7534 0.00705 0.00183 -0.0836 0.3432 1.0000
3.000 0.7785 0.00718 0.00191 -0.0831 0.3313 1.0000
3.250 0.8037 0.00731 0.00199 -0.0825 0.3205 1.0000
3.500 0.8288 0.00744 0.00209 -0.0820 0.3121 1.0000
3.750 0.8536 0.00759 0.00219 -0.0814 0.2981 1.0000
4.000 0.8778 0.00780 0.00229 -0.0807 0.2760 1.0000
4.250 0.8972 0.00846 0.00256 -0.0793 0.1952 1.0000
4.500 0.9170 0.00911 0.00295 -0.0780 0.1512 1.0000
4.750 0.9301 0.01052 0.00370 -0.0755 0.0242 1.0000
5.000 0.9533 0.01086 0.00402 -0.0745 0.0147 1.0000
5.250 0.9770 0.01112 0.00434 -0.0737 0.0132 1.0000
5.500 1.0004 0.01142 0.00471 -0.0728 0.0123 1.0000
5.750 1.0231 0.01180 0.00515 -0.0718 0.0112 1.0000
6.000 1.0448 0.01227 0.00570 -0.0706 0.0100 1.0000
6.250 1.0641 0.01300 0.00653 -0.0690 0.0087 1.0000
6.500 1.0801 0.01404 0.00771 -0.0668 0.0082 1.0000
6.750 1.0990 0.01471 0.00845 -0.0651 0.0079 1.0000
7.000 1.1194 0.01521 0.00901 -0.0638 0.0076 1.0000
7.250 1.1389 0.01577 0.00963 -0.0622 0.0071 1.0000
7.500 1.1553 0.01659 0.01052 -0.0602 0.0068 1.0000
7.750 1.1706 0.01748 0.01148 -0.0580 0.0064 1.0000
8.000 1.1838 0.01855 0.01263 -0.0553 0.0061 1.0000
8.250 1.1949 0.01988 0.01405 -0.0524 0.0061 1.0000
8.500 1.2072 0.02121 0.01545 -0.0497 0.0061 1.0000
8.750 1.2213 0.02235 0.01668 -0.0475 0.0059 1.0000
9.000 1.2355 0.02356 0.01795 -0.0454 0.0057 1.0000
9.250 1.2501 0.02432 0.01872 -0.0436 0.0053 1.0000
9.500 1.2641 0.02703 0.02165 -0.0411 0.0058 1.0000
9.750 1.2786 0.02939 0.02419 -0.0390 0.0061 1.0000
10.000 1.2915 0.03218 0.02719 -0.0368 0.0063 1.0000
10.250 1.3011 0.03358 0.02871 -0.0343 0.0059 1.0000
11.250 1.2965 0.04136 0.03702 -0.0201 0.0042 1.0000
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