dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 100,000 Max Cl/Cd: 31.65 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dh4009sm-il-100000-n5.txt Download as CSV file: xf-dh4009sm-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6987 0.07496 0.06906 -0.0209 1.0000 0.0498
-6.500 -0.6443 0.04761 0.04085 -0.0138 1.0000 0.0324
-6.250 -0.6323 0.04366 0.03649 -0.0114 1.0000 0.0279
-6.000 -0.6119 0.04139 0.03369 -0.0088 1.0000 0.0235
-5.750 -0.5978 0.03815 0.03017 -0.0071 1.0000 0.0228
-5.500 -0.5814 0.03538 0.02709 -0.0053 1.0000 0.0223
-5.250 -0.5628 0.03303 0.02439 -0.0036 1.0000 0.0224
-5.000 -0.5419 0.03173 0.02268 -0.0018 1.0000 0.0239
-4.750 -0.5220 0.02958 0.02017 -0.0002 1.0000 0.0250
-4.500 -0.4999 0.02782 0.01809 0.0012 1.0000 0.0248
-4.000 -0.4536 0.02455 0.01439 0.0034 1.0000 0.0245
-3.750 -0.4299 0.02290 0.01267 0.0044 1.0000 0.0245
-3.500 -0.4069 0.02131 0.01102 0.0055 1.0000 0.0247
-3.250 -0.3858 0.01989 0.00961 0.0068 1.0000 0.0251
-3.000 -0.3672 0.01871 0.00845 0.0084 1.0000 0.0259
-2.750 -0.3493 0.01780 0.00746 0.0101 1.0000 0.0270
-2.500 -0.3307 0.01714 0.00673 0.0116 1.0000 0.0293
-2.250 -0.3110 0.01669 0.00618 0.0129 1.0000 0.0348
-2.000 -0.2913 0.01614 0.00551 0.0142 1.0000 0.0403
-1.750 -0.2706 0.01569 0.00498 0.0154 1.0000 0.0517
-1.500 -0.2647 0.01263 0.00506 0.0197 0.9991 0.7494
-1.250 -0.2471 0.01299 0.00573 0.0248 0.9911 0.8741
-1.000 -0.2138 0.01319 0.00582 0.0245 0.9849 0.9045
-0.750 -0.1752 0.01318 0.00565 0.0219 0.9784 0.9125
-0.500 -0.1367 0.01318 0.00553 0.0192 0.9716 0.9201
-0.250 -0.0963 0.01318 0.00541 0.0162 0.9661 0.9279
0.000 -0.0561 0.01319 0.00537 0.0132 0.9596 0.9346
0.250 -0.0138 0.01319 0.00534 0.0097 0.9545 0.9416
0.500 0.0279 0.01320 0.00535 0.0064 0.9481 0.9476
0.750 0.0717 0.01321 0.00538 0.0026 0.9424 0.9534
1.000 0.1151 0.01322 0.00544 -0.0011 0.9360 0.9590
1.250 0.1601 0.01321 0.00552 -0.0051 0.9287 0.9634
1.500 0.2036 0.01319 0.00562 -0.0087 0.9191 0.9683
1.750 0.2488 0.01314 0.00571 -0.0125 0.9082 0.9721
2.000 0.2943 0.01309 0.00583 -0.0164 0.8962 0.9752
2.250 0.3377 0.01300 0.00596 -0.0194 0.8747 0.9786
2.500 0.3781 0.01276 0.00566 -0.0202 0.8005 0.9798
2.750 0.4064 0.01284 0.00541 -0.0188 0.6682 0.9853
3.000 0.4159 0.01571 0.00555 -0.0157 0.1167 0.9919
3.250 0.4446 0.01695 0.00645 -0.0166 0.0595 0.9988
3.500 0.4633 0.01759 0.00727 -0.0150 0.0505 1.0000
3.750 0.4777 0.01829 0.00802 -0.0127 0.0429 1.0000
4.000 0.4926 0.01899 0.00882 -0.0104 0.0386 1.0000
4.250 0.5073 0.01988 0.00975 -0.0080 0.0359 1.0000
4.500 0.5229 0.02117 0.01102 -0.0059 0.0338 1.0000
4.750 0.5424 0.02262 0.01253 -0.0044 0.0320 1.0000
5.000 0.5633 0.02358 0.01374 -0.0029 0.0288 1.0000
5.250 0.5845 0.02497 0.01530 -0.0016 0.0267 1.0000
5.500 0.6060 0.02671 0.01726 -0.0003 0.0258 1.0000
5.750 0.6265 0.02864 0.01946 0.0012 0.0252 1.0000
6.000 0.6455 0.03079 0.02195 0.0029 0.0248 1.0000
6.250 0.6627 0.03320 0.02475 0.0049 0.0247 1.0000
6.500 0.6780 0.03592 0.02791 0.0072 0.0248 1.0000
6.750 0.6909 0.03897 0.03142 0.0096 0.0251 1.0000
7.000 0.7015 0.04235 0.03525 0.0121 0.0255 1.0000
7.250 0.7109 0.04539 0.03869 0.0143 0.0250 1.0000
7.500 0.7214 0.04763 0.04102 0.0154 0.0234 1.0000
8.000 0.7228 0.05568 0.04958 0.0191 0.0218 1.0000
8.250 0.7231 0.05937 0.05355 0.0209 0.0217 1.0000
8.750 0.7223 0.06651 0.06112 0.0235 0.0224 1.0000
9.250 0.6879 0.07657 0.07167 0.0236 0.0247 1.0000
9.500 0.6716 0.08299 0.07816 0.0193 0.0255 1.0000
9.750 0.6611 0.09064 0.08579 0.0127 0.0265 1.0000
10.000 0.6552 0.09713 0.09223 0.0082 0.0275 1.0000
10.250 0.6515 0.10273 0.09779 0.0050 0.0286 1.0000
10.500 0.6495 0.10779 0.10282 0.0028 0.0300 1.0000
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Polar data table (+)
Polar graphs
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