dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 500,000 Max Cl/Cd: 42.09 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dh4009sm-il-500000-n5.txt Download as CSV file: xf-dh4009sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: dh4009sm
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6452 0.08133 0.07898 -0.0206 1.0000 0.0087
-9.000 -0.6570 0.07675 0.07435 -0.0226 1.0000 0.0087
-8.750 -0.6706 0.07312 0.07067 -0.0221 1.0000 0.0087
-8.500 -0.6788 0.06928 0.06673 -0.0212 1.0000 0.0087
-8.250 -0.6829 0.06534 0.06268 -0.0203 1.0000 0.0087
-8.000 -0.6843 0.06144 0.05865 -0.0190 1.0000 0.0087
-7.750 -0.6830 0.05763 0.05468 -0.0176 1.0000 0.0087
-7.500 -0.6792 0.05392 0.05081 -0.0159 1.0000 0.0087
-5.750 -0.6149 0.02994 0.02528 -0.0015 1.0000 0.0080
-5.500 -0.5998 0.02719 0.02225 0.0006 1.0000 0.0077
-5.250 -0.5818 0.02462 0.01941 0.0026 0.9999 0.0074
-5.000 -0.5516 0.02181 0.01628 0.0021 0.9981 0.0072
-4.750 -0.5211 0.01931 0.01347 0.0018 0.9955 0.0071
-4.500 -0.4946 0.01729 0.01122 0.0023 0.9868 0.0071
-4.250 -0.4665 0.01563 0.00936 0.0025 0.9784 0.0074
-4.000 -0.4363 0.01438 0.00797 0.0020 0.9721 0.0079
-3.750 -0.4041 0.01344 0.00694 0.0009 0.9666 0.0084
-3.500 -0.3715 0.01273 0.00616 -0.0003 0.9597 0.0087
-3.250 -0.3387 0.01150 0.00488 -0.0019 0.9541 0.0100
-3.000 -0.3035 0.01075 0.00405 -0.0038 0.9468 0.0103
-2.750 -0.2646 0.01009 0.00332 -0.0066 0.9407 0.0105
-2.500 -0.2243 0.00958 0.00274 -0.0097 0.9330 0.0109
-2.250 -0.1827 0.00919 0.00228 -0.0131 0.9249 0.0120
-2.000 -0.1431 0.00893 0.00191 -0.0160 0.9140 0.0145
-1.750 -0.1073 0.00863 0.00165 -0.0181 0.9017 0.0409
-1.250 -0.0760 0.00588 0.00127 -0.0143 0.8714 0.7269
-1.000 -0.0491 0.00586 0.00127 -0.0141 0.8601 0.7525
-0.750 -0.0210 0.00587 0.00123 -0.0142 0.8498 0.7602
-0.500 0.0069 0.00589 0.00120 -0.0143 0.8401 0.7664
-0.250 0.0343 0.00591 0.00119 -0.0142 0.8298 0.7731
0.000 0.0610 0.00594 0.00118 -0.0140 0.8166 0.7796
0.250 0.0874 0.00598 0.00118 -0.0137 0.8021 0.7862
0.500 0.1137 0.00601 0.00119 -0.0134 0.7896 0.7929
0.750 0.1402 0.00603 0.00123 -0.0131 0.7793 0.7996
1.000 0.1668 0.00606 0.00126 -0.0129 0.7694 0.8063
1.250 0.1924 0.00610 0.00131 -0.0124 0.7525 0.8132
1.500 0.2163 0.00619 0.00133 -0.0115 0.7217 0.8203
1.750 0.2387 0.00633 0.00135 -0.0102 0.6764 0.8275
2.000 0.2573 0.00666 0.00137 -0.0081 0.5817 0.8352
2.250 0.2699 0.00759 0.00155 -0.0052 0.3874 0.8438
2.500 0.2866 0.00849 0.00184 -0.0034 0.2147 0.8520
2.750 0.3053 0.00929 0.00215 -0.0019 0.0752 0.8609
3.000 0.3291 0.00962 0.00239 -0.0012 0.0414 0.8693
3.250 0.3539 0.00984 0.00262 -0.0007 0.0297 0.8780
3.500 0.3781 0.01015 0.00295 0.0000 0.0220 0.8876
3.750 0.4037 0.01033 0.00321 0.0004 0.0190 0.8969
4.000 0.4288 0.01060 0.00353 0.0008 0.0160 0.9071
4.250 0.4522 0.01115 0.00419 0.0017 0.0136 0.9184
4.500 0.4783 0.01151 0.00463 0.0019 0.0128 0.9302
4.750 0.5055 0.01202 0.00525 0.0018 0.0118 0.9418
5.000 0.5346 0.01270 0.00604 0.0013 0.0110 0.9521
5.250 0.5645 0.01353 0.00698 0.0005 0.0105 0.9617
5.750 0.6266 0.01516 0.00879 -0.0016 0.0094 0.9782
6.000 0.6567 0.01600 0.00971 -0.0027 0.0087 0.9862
6.250 0.6838 0.01807 0.01202 -0.0030 0.0083 0.9933
6.500 0.7117 0.01968 0.01389 -0.0034 0.0080 1.0000
6.750 0.7299 0.02095 0.01538 -0.0017 0.0078 1.0000
7.000 0.7465 0.02278 0.01749 0.0003 0.0075 1.0000
7.250 0.7599 0.02556 0.02065 0.0030 0.0072 1.0000
7.500 0.7676 0.02978 0.02536 0.0065 0.0070 1.0000
7.750 0.7713 0.03475 0.03079 0.0104 0.0069 1.0000
8.000 0.7738 0.03956 0.03598 0.0137 0.0069 1.0000
8.250 0.7761 0.04410 0.04083 0.0165 0.0066 1.0000
8.500 0.7773 0.04842 0.04541 0.0188 0.0063 1.0000
8.750 0.7755 0.05277 0.04998 0.0208 0.0061 1.0000
9.000 0.7685 0.05751 0.05492 0.0225 0.0061 1.0000
9.250 0.7575 0.06224 0.05981 0.0237 0.0060 1.0000
9.500 0.7395 0.06671 0.06440 0.0248 0.0061 1.0000
9.750 0.7198 0.07220 0.06999 0.0227 0.0061 1.0000
10.000 0.7008 0.08083 0.07868 0.0148 0.0063 1.0000
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Polar data table (+)
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