dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 100,000 Max Cl/Cd: 27.56 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dh4009sm-il-100000.txt Download as CSV file: xf-dh4009sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5006 0.12328 0.11833 -0.0107 1.0000 0.0755
-11.250 -0.5134 0.11992 0.11502 -0.0140 1.0000 0.0763
-11.000 -0.6327 0.12601 0.12081 0.0008 1.0000 0.0666
-10.750 -0.6284 0.12221 0.11702 0.0003 1.0000 0.0695
-10.500 -0.6285 0.11809 0.11293 -0.0017 1.0000 0.0722
-10.250 -0.6334 0.11365 0.10855 -0.0054 1.0000 0.0747
-10.000 -0.6439 0.10872 0.10370 -0.0114 1.0000 0.0758
-9.750 -0.6567 0.10317 0.09821 -0.0179 1.0000 0.0762
-9.500 -0.6731 0.09873 0.09376 -0.0218 1.0000 0.0763
-9.250 -0.6401 0.09525 0.09027 -0.0133 1.0000 0.0829
-9.000 -0.6483 0.09002 0.08509 -0.0174 1.0000 0.0848
-8.750 -0.6622 0.08535 0.08043 -0.0205 1.0000 0.0860
-8.500 -0.6787 0.08149 0.07658 -0.0216 1.0000 0.0875
-8.250 -0.7004 0.07875 0.07361 -0.0223 1.0000 0.0895
-8.000 -0.6995 0.07333 0.06820 -0.0220 1.0000 0.0922
-7.750 -0.6894 0.06970 0.06458 -0.0209 1.0000 0.0982
-7.500 -0.7083 0.06814 0.06245 -0.0197 1.0000 0.1042
-7.250 -0.6885 0.06256 0.05722 -0.0192 1.0000 0.1116
-7.000 -0.6874 0.05907 0.05357 -0.0180 1.0000 0.1214
-6.750 -0.6827 0.05591 0.05029 -0.0166 1.0000 0.1346
-4.500 -0.5228 0.01432 0.00655 -0.0018 1.0000 0.1331
-4.250 -0.4998 0.02711 0.01792 0.0004 1.0000 0.0840
-4.000 -0.4713 0.02515 0.01557 0.0020 1.0000 0.0704
-3.750 -0.4446 0.02439 0.01436 0.0039 1.0000 0.0627
-3.500 -0.4180 0.02213 0.01210 0.0046 1.0000 0.0600
-3.250 -0.3929 0.02064 0.01057 0.0057 1.0000 0.0580
-3.000 -0.3697 0.01940 0.00929 0.0070 1.0000 0.0572
-2.750 -0.3494 0.01834 0.00826 0.0086 1.0000 0.0576
-2.500 -0.3310 0.01747 0.00738 0.0105 1.0000 0.0594
-2.250 -0.3126 0.01670 0.00653 0.0122 1.0000 0.0654
-2.000 -0.2932 0.01603 0.00579 0.0137 1.0000 0.0774
-1.750 -0.1510 0.01613 0.00875 0.0058 1.0000 0.9647
-1.500 -0.1148 0.01580 0.00825 0.0031 1.0000 0.9728
-1.250 -0.0737 0.01547 0.00778 -0.0006 1.0000 0.9798
-1.000 -0.0339 0.01515 0.00735 -0.0041 1.0000 0.9871
-0.750 0.0069 0.01486 0.00699 -0.0079 1.0000 0.9947
-0.500 0.0435 0.01456 0.00666 -0.0109 1.0000 1.0000
-0.250 0.0508 0.01436 0.00651 -0.0083 1.0000 1.0000
0.000 0.0512 0.01425 0.00645 -0.0047 1.0000 1.0000
0.250 0.0396 0.01424 0.00648 0.0009 1.0000 1.0000
0.500 0.0215 0.01424 0.00650 0.0074 1.0000 1.0000
0.750 0.0069 0.01422 0.00646 0.0133 1.0000 1.0000
1.000 0.0028 0.01425 0.00647 0.0176 1.0000 1.0000
1.250 0.0102 0.01440 0.00659 0.0199 1.0000 1.0000
1.500 0.0238 0.01464 0.00682 0.0211 1.0000 1.0000
1.750 0.0696 0.01502 0.00728 0.0162 0.9920 1.0000
2.000 0.1181 0.01535 0.00774 0.0110 0.9821 1.0000
2.250 0.1653 0.01564 0.00816 0.0062 0.9715 1.0000
2.500 0.2129 0.01589 0.00860 0.0014 0.9604 1.0000
2.750 0.2650 0.01605 0.00906 -0.0039 0.9479 1.0000
3.000 0.4363 0.01583 0.00609 -0.0191 0.1382 1.0000
3.250 0.4484 0.01712 0.00710 -0.0161 0.0986 1.0000
3.500 0.4614 0.01810 0.00812 -0.0134 0.0841 1.0000
3.750 0.4760 0.01903 0.00903 -0.0109 0.0744 1.0000
4.000 0.4938 0.02053 0.01045 -0.0089 0.0703 1.0000
4.250 0.5164 0.02191 0.01192 -0.0074 0.0679 1.0000
4.500 0.5398 0.02342 0.01356 -0.0061 0.0651 1.0000
4.750 0.5617 0.02543 0.01554 -0.0053 0.0597 1.0000
5.000 0.5846 0.02748 0.01782 -0.0039 0.0597 1.0000
5.250 0.6063 0.02923 0.02025 -0.0013 0.0636 1.0000
5.500 0.6265 0.03229 0.02369 0.0008 0.0691 1.0000
5.750 0.6477 0.03596 0.02788 0.0033 0.0836 1.0000
8.500 0.7367 0.07979 0.07479 0.0207 0.1117 1.0000
8.750 0.7036 0.08262 0.07790 0.0192 0.1104 1.0000
9.000 0.6785 0.08709 0.08241 0.0160 0.1090 1.0000
9.250 0.6623 0.09303 0.08830 0.0096 0.1066 1.0000
9.500 0.6976 0.09526 0.09052 0.0190 0.0981 1.0000
9.750 0.6756 0.10078 0.09602 0.0123 0.0978 1.0000
10.000 0.6554 0.10676 0.10190 0.0037 0.0963 1.0000
|
Polar data table (+)
Polar graphs
<< Back to dh4009sm (dh4009sm-il)