dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 53.37 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dh4009sm-il-1000000-n5.txt Download as CSV file: xf-dh4009sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6851 0.07870 0.07707 -0.0174 1.0000 0.0036
-9.000 -0.7027 0.07401 0.07233 -0.0192 1.0000 0.0036
-8.750 -0.7164 0.06978 0.06804 -0.0188 1.0000 0.0036
-8.500 -0.7234 0.06522 0.06337 -0.0185 1.0000 0.0036
-8.250 -0.7266 0.06071 0.05874 -0.0177 1.0000 0.0036
-8.000 -0.7266 0.05627 0.05415 -0.0166 1.0000 0.0038
-7.750 -0.7235 0.05186 0.04957 -0.0150 1.0000 0.0040
-7.500 -0.7178 0.04747 0.04498 -0.0130 1.0000 0.0042
-7.250 -0.7091 0.04347 0.04078 -0.0109 1.0000 0.0044
-7.000 -0.6985 0.03998 0.03709 -0.0087 1.0000 0.0045
-6.750 -0.6866 0.03671 0.03362 -0.0065 1.0000 0.0046
-6.500 -0.6711 0.03408 0.03081 -0.0045 1.0000 0.0048
-5.750 -0.6065 0.02437 0.02028 -0.0024 0.9970 0.0048
-5.500 -0.5819 0.02059 0.01612 -0.0019 0.9939 0.0047
-5.250 -0.5650 0.01781 0.01305 0.0007 0.9761 0.0046
-5.000 -0.5355 0.01529 0.01024 0.0005 0.9700 0.0047
-4.750 -0.5031 0.01369 0.00845 -0.0006 0.9642 0.0048
-4.500 -0.4676 0.01278 0.00742 -0.0026 0.9579 0.0049
-4.250 -0.4325 0.01093 0.00540 -0.0046 0.9521 0.0057
-4.000 -0.3913 0.01035 0.00478 -0.0081 0.9451 0.0061
-3.750 -0.3467 0.00975 0.00413 -0.0123 0.9383 0.0066
-3.500 -0.3009 0.00916 0.00347 -0.0169 0.9292 0.0069
-3.250 -0.2582 0.00878 0.00301 -0.0207 0.9159 0.0076
-3.000 -0.2229 0.00844 0.00258 -0.0227 0.8992 0.0079
-2.750 -0.1940 0.00815 0.00217 -0.0231 0.8821 0.0080
-2.500 -0.1673 0.00794 0.00186 -0.0230 0.8673 0.0082
-2.250 -0.1412 0.00779 0.00162 -0.0227 0.8541 0.0085
-2.000 -0.1153 0.00764 0.00138 -0.0223 0.8423 0.0102
-1.750 -0.0894 0.00753 0.00125 -0.0220 0.8314 0.0172
-1.500 -0.0647 0.00729 0.00114 -0.0215 0.8214 0.0681
-1.250 -0.0613 0.00521 0.00073 -0.0175 0.8103 0.5811
-1.000 -0.0408 0.00490 0.00072 -0.0159 0.8005 0.6803
-0.500 0.0090 0.00485 0.00070 -0.0147 0.7728 0.7235
-0.250 0.0353 0.00487 0.00068 -0.0144 0.7598 0.7298
0.250 0.0888 0.00489 0.00068 -0.0141 0.7413 0.7422
0.750 0.1417 0.00495 0.00071 -0.0136 0.7184 0.7549
1.000 0.1663 0.00504 0.00072 -0.0129 0.6869 0.7617
1.250 0.1898 0.00519 0.00075 -0.0120 0.6403 0.7679
1.500 0.2083 0.00569 0.00081 -0.0101 0.5144 0.7751
1.750 0.2256 0.00644 0.00099 -0.0082 0.3522 0.7817
2.000 0.2465 0.00697 0.00115 -0.0071 0.2406 0.7890
2.250 0.2671 0.00756 0.00136 -0.0059 0.1243 0.7958
2.500 0.2899 0.00798 0.00156 -0.0051 0.0515 0.8031
2.750 0.3151 0.00817 0.00170 -0.0046 0.0334 0.8100
3.000 0.3406 0.00834 0.00185 -0.0043 0.0232 0.8174
3.250 0.3662 0.00848 0.00202 -0.0039 0.0191 0.8245
3.500 0.3917 0.00866 0.00220 -0.0036 0.0151 0.8323
3.750 0.4170 0.00884 0.00245 -0.0031 0.0132 0.8399
4.000 0.4425 0.00901 0.00267 -0.0028 0.0119 0.8478
4.250 0.4675 0.00921 0.00291 -0.0023 0.0105 0.8563
4.500 0.4920 0.00947 0.00322 -0.0017 0.0092 0.8648
5.000 0.5384 0.01030 0.00429 0.0000 0.0080 0.8845
5.250 0.5620 0.01065 0.00473 0.0008 0.0078 0.8952
5.500 0.5860 0.01098 0.00514 0.0014 0.0074 0.9073
5.750 0.6095 0.01142 0.00569 0.0022 0.0072 0.9208
6.000 0.6337 0.01196 0.00636 0.0027 0.0070 0.9359
6.250 0.6611 0.01260 0.00712 0.0025 0.0067 0.9511
6.500 0.6925 0.01337 0.00802 0.0013 0.0065 0.9637
6.750 0.7256 0.01413 0.00889 -0.0004 0.0062 0.9738
7.000 0.7583 0.01489 0.00974 -0.0020 0.0059 0.9825
7.250 0.7893 0.01557 0.01051 -0.0032 0.0056 0.9911
7.500 0.8173 0.01627 0.01130 -0.0038 0.0053 0.9995
7.750 0.8361 0.01738 0.01256 -0.0023 0.0050 1.0000
8.000 0.8421 0.02122 0.01693 0.0014 0.0047 1.0000
8.250 0.8594 0.02249 0.01842 0.0030 0.0046 1.0000
8.500 0.8755 0.02402 0.02015 0.0047 0.0045 1.0000
8.750 0.8864 0.02669 0.02314 0.0072 0.0043 1.0000
9.250 0.8276 0.04925 0.04707 0.0202 0.0040 1.0000
9.500 0.8118 0.05551 0.05357 0.0227 0.0039 1.0000
9.750 0.7931 0.06089 0.05912 0.0245 0.0039 1.0000
10.000 0.7703 0.06568 0.06403 0.0255 0.0039 1.0000
10.250 0.7477 0.07180 0.07024 0.0222 0.0040 1.0000
10.500 0.7267 0.08257 0.08106 0.0114 0.0041 1.0000
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Polar data table (+)
Polar graphs
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