BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.25 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13006-il-1000000-n5.txt Download as CSV file: xf-v13006-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V13006-.7 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6662 0.09297 0.09136 0.0208 1.0000 0.0061
-8.500 -0.6670 0.08828 0.08668 0.0176 1.0000 0.0060
-8.250 -0.6692 0.08314 0.08156 0.0130 1.0000 0.0060
-8.000 -0.6668 0.07670 0.07511 0.0052 1.0000 0.0059
-7.750 -0.6612 0.06989 0.06825 -0.0016 1.0000 0.0058
-7.500 -0.6538 0.06298 0.06124 -0.0069 1.0000 0.0058
-7.250 -0.6446 0.05584 0.05394 -0.0109 1.0000 0.0059
-7.000 -0.6346 0.04778 0.04564 -0.0137 1.0000 0.0061
-6.750 -0.6240 0.03846 0.03592 -0.0148 1.0000 0.0065
-6.500 -0.6124 0.02897 0.02589 -0.0142 1.0000 0.0067
-6.250 -0.6047 0.01766 0.01342 -0.0120 1.0000 0.0069
-6.000 -0.5827 0.01522 0.01060 -0.0113 1.0000 0.0071
-5.750 -0.5579 0.01418 0.00941 -0.0108 1.0000 0.0073
-5.500 -0.5330 0.01316 0.00823 -0.0103 1.0000 0.0074
-5.250 -0.5076 0.01239 0.00734 -0.0099 1.0000 0.0076
-5.000 -0.4822 0.01170 0.00656 -0.0094 1.0000 0.0078
-4.750 -0.4567 0.01110 0.00588 -0.0089 1.0000 0.0081
-4.500 -0.4313 0.01054 0.00526 -0.0084 1.0000 0.0084
-4.250 -0.4059 0.01004 0.00469 -0.0079 1.0000 0.0088
-4.000 -0.3807 0.00960 0.00420 -0.0073 1.0000 0.0091
-3.750 -0.3555 0.00923 0.00379 -0.0068 1.0000 0.0094
-3.500 -0.3229 0.00885 0.00339 -0.0078 0.9962 0.0097
-3.250 -0.2891 0.00853 0.00302 -0.0092 0.9890 0.0099
-3.000 -0.2566 0.00799 0.00243 -0.0103 0.9796 0.0106
-2.750 -0.2236 0.00772 0.00216 -0.0114 0.9649 0.0114
-2.500 -0.1937 0.00754 0.00194 -0.0117 0.9376 0.0124
-2.250 -0.1687 0.00745 0.00172 -0.0107 0.8949 0.0131
-2.000 -0.1438 0.00741 0.00152 -0.0098 0.8487 0.0137
-1.750 -0.1180 0.00736 0.00131 -0.0093 0.8081 0.0147
-1.500 -0.0917 0.00735 0.00116 -0.0088 0.7639 0.0169
-1.250 -0.0652 0.00740 0.00104 -0.0084 0.7148 0.0196
-1.000 -0.0383 0.00741 0.00095 -0.0082 0.6732 0.0273
-0.750 -0.0114 0.00748 0.00087 -0.0080 0.6223 0.0359
-0.500 0.0157 0.00751 0.00080 -0.0078 0.5767 0.0527
-0.250 0.0426 0.00737 0.00075 -0.0077 0.5419 0.1200
0.000 0.0673 0.00648 0.00066 -0.0077 0.5090 0.4183
0.250 0.0901 0.00572 0.00064 -0.0071 0.4581 0.6995
0.500 0.1112 0.00542 0.00070 -0.0056 0.3982 0.8606
0.750 0.1352 0.00546 0.00074 -0.0045 0.3570 0.9135
1.000 0.1618 0.00567 0.00080 -0.0041 0.2997 0.9548
1.250 0.1998 0.00605 0.00088 -0.0065 0.2218 0.9872
1.500 0.2346 0.00636 0.00095 -0.0082 0.1659 0.9951
1.750 0.2678 0.00656 0.00102 -0.0095 0.1407 0.9982
2.000 0.2971 0.00692 0.00113 -0.0100 0.0813 1.0000
2.250 0.3224 0.00728 0.00130 -0.0095 0.0342 1.0000
2.500 0.3484 0.00742 0.00140 -0.0091 0.0273 1.0000
2.750 0.3744 0.00764 0.00154 -0.0087 0.0143 1.0000
3.000 0.4007 0.00780 0.00168 -0.0084 0.0131 1.0000
3.250 0.4271 0.00796 0.00184 -0.0080 0.0125 1.0000
3.500 0.4536 0.00815 0.00202 -0.0077 0.0117 1.0000
3.750 0.4802 0.00836 0.00224 -0.0074 0.0111 1.0000
4.000 0.5068 0.00859 0.00249 -0.0072 0.0108 1.0000
4.250 0.5333 0.00884 0.00277 -0.0069 0.0106 1.0000
4.500 0.5599 0.00909 0.00304 -0.0066 0.0105 1.0000
4.750 0.5865 0.00936 0.00333 -0.0064 0.0103 1.0000
5.000 0.6130 0.00966 0.00365 -0.0061 0.0101 1.0000
5.250 0.6394 0.00999 0.00402 -0.0059 0.0099 1.0000
5.500 0.6656 0.01036 0.00443 -0.0056 0.0096 1.0000
5.750 0.6917 0.01077 0.00489 -0.0053 0.0093 1.0000
6.000 0.7176 0.01122 0.00539 -0.0050 0.0091 1.0000
6.250 0.7433 0.01172 0.00595 -0.0047 0.0089 1.0000
6.500 0.7689 0.01220 0.00648 -0.0044 0.0086 1.0000
6.750 0.7943 0.01270 0.00702 -0.0041 0.0083 1.0000
7.000 0.8194 0.01330 0.00767 -0.0038 0.0082 1.0000
7.250 0.8440 0.01398 0.00842 -0.0034 0.0080 1.0000
7.500 0.8681 0.01478 0.00929 -0.0030 0.0079 1.0000
7.750 0.8912 0.01583 0.01043 -0.0025 0.0077 1.0000
8.000 0.9119 0.01755 0.01232 -0.0017 0.0075 1.0000
8.250 0.9360 0.01827 0.01315 -0.0013 0.0074 1.0000
8.500 0.9597 0.01905 0.01405 -0.0009 0.0074 1.0000
8.750 0.9829 0.01993 0.01506 -0.0004 0.0073 1.0000
9.000 1.0055 0.02092 0.01620 0.0001 0.0072 1.0000
9.250 1.0272 0.02206 0.01750 0.0006 0.0070 1.0000
9.500 1.0477 0.02340 0.01904 0.0013 0.0069 1.0000
9.750 1.0670 0.02494 0.02079 0.0019 0.0067 1.0000
10.000 1.0855 0.02649 0.02255 0.0026 0.0064 1.0000
10.250 1.1027 0.02815 0.02442 0.0033 0.0062 1.0000
10.500 1.1173 0.03016 0.02665 0.0041 0.0060 1.0000
10.750 1.1291 0.03245 0.02918 0.0050 0.0059 1.0000
11.000 1.1378 0.03501 0.03198 0.0058 0.0058 1.0000
11.250 1.1426 0.03781 0.03502 0.0066 0.0057 1.0000
11.500 1.1417 0.04101 0.03845 0.0074 0.0057 1.0000
11.750 1.1294 0.04460 0.04225 0.0083 0.0056 1.0000
12.000 1.1078 0.05051 0.04839 0.0047 0.0056 1.0000
12.250 1.0639 0.06795 0.06618 -0.0131 0.0057 1.0000
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Polar data table (+)
Polar graphs
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