dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 200,000 Max Cl/Cd: 40.3 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dh4009sm-il-200000.txt Download as CSV file: xf-dh4009sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6365 0.08905 0.08551 -0.0159 1.0000 0.0303
-9.000 -0.6465 0.08323 0.07968 -0.0207 1.0000 0.0302
-8.750 -0.6596 0.07869 0.07512 -0.0228 1.0000 0.0301
-8.500 -0.6718 0.07494 0.07131 -0.0226 1.0000 0.0305
-8.250 -0.6782 0.07108 0.06737 -0.0225 1.0000 0.0313
-8.000 -0.6814 0.06735 0.06352 -0.0219 1.0000 0.0325
-7.750 -0.6808 0.06390 0.05988 -0.0210 1.0000 0.0340
-7.500 -0.6762 0.06294 0.05846 -0.0186 1.0000 0.0360
-7.250 -0.6706 0.06143 0.05658 -0.0163 1.0000 0.0364
-7.000 -0.6709 0.05584 0.05075 -0.0146 1.0000 0.0370
-6.750 -0.6643 0.04940 0.04439 -0.0142 1.0000 0.0385
-6.500 -0.6533 0.04614 0.04109 -0.0132 1.0000 0.0401
-6.250 -0.6412 0.04341 0.03821 -0.0116 1.0000 0.0424
-6.000 -0.6271 0.04107 0.03561 -0.0098 1.0000 0.0460
-3.500 -0.4323 0.01995 0.01195 0.0080 1.0000 0.0462
-3.250 -0.4074 0.01826 0.01011 0.0093 1.0000 0.0418
-3.000 -0.3845 0.01784 0.00949 0.0110 1.0000 0.0372
-2.750 -0.3625 0.01667 0.00830 0.0122 1.0000 0.0358
-2.500 -0.3420 0.01555 0.00719 0.0135 1.0000 0.0351
-2.250 -0.3222 0.01472 0.00637 0.0149 1.0000 0.0350
-2.000 -0.3025 0.01407 0.00571 0.0161 1.0000 0.0356
-1.750 -0.2823 0.01356 0.00514 0.0171 1.0000 0.0369
-1.500 -0.2523 0.01294 0.00438 0.0162 0.9980 0.0463
-1.250 -0.2395 0.00980 0.00437 0.0194 0.9958 0.8018
-1.000 -0.2189 0.01012 0.00490 0.0230 0.9881 0.8881
-0.750 -0.1951 0.01044 0.00526 0.0258 0.9815 0.9309
-0.500 -0.1546 0.01049 0.00521 0.0229 0.9766 0.9394
-0.250 -0.1126 0.01051 0.00514 0.0195 0.9715 0.9464
0.000 -0.0660 0.01055 0.00513 0.0152 0.9682 0.9518
0.250 -0.0234 0.01056 0.00512 0.0117 0.9628 0.9583
0.500 0.0252 0.01058 0.00513 0.0069 0.9587 0.9617
0.750 0.0760 0.01053 0.00510 0.0017 0.9553 0.9646
1.000 0.1255 0.01046 0.00507 -0.0031 0.9492 0.9677
1.250 0.1764 0.01035 0.00504 -0.0082 0.9430 0.9701
1.500 0.2273 0.01026 0.00504 -0.0133 0.9364 0.9719
1.750 0.2801 0.01009 0.00497 -0.0185 0.9242 0.9725
2.000 0.3286 0.00984 0.00478 -0.0218 0.8861 0.9727
2.250 0.3666 0.00976 0.00464 -0.0230 0.8335 0.9757
2.500 0.3957 0.00982 0.00444 -0.0221 0.7422 0.9814
2.750 0.4036 0.01197 0.00435 -0.0179 0.2370 0.9881
3.000 0.4288 0.01396 0.00546 -0.0183 0.0589 0.9940
3.250 0.4642 0.01479 0.00639 -0.0202 0.0488 0.9986
3.500 0.4845 0.01603 0.00763 -0.0191 0.0445 1.0000
3.750 0.5015 0.01647 0.00814 -0.0172 0.0397 1.0000
4.000 0.5181 0.01733 0.00902 -0.0152 0.0371 1.0000
4.250 0.5358 0.01848 0.01020 -0.0134 0.0355 1.0000
4.500 0.5553 0.01990 0.01172 -0.0117 0.0350 1.0000
4.750 0.5757 0.02143 0.01346 -0.0098 0.0359 1.0000
5.000 0.5969 0.02390 0.01640 -0.0075 0.0401 1.0000
5.500 0.6438 0.03195 0.02587 0.0001 0.0941 1.0000
5.750 0.6531 0.03355 0.02758 0.0027 0.0799 1.0000
6.000 0.6677 0.03585 0.02987 0.0043 0.0742 1.0000
6.250 0.6741 0.03783 0.03228 0.0078 0.0650 1.0000
6.500 0.6875 0.04036 0.03486 0.0095 0.0613 1.0000
6.750 0.6925 0.04821 0.04261 0.0102 0.0585 1.0000
7.000 0.7013 0.04616 0.04134 0.0148 0.0521 1.0000
7.250 0.7105 0.04898 0.04433 0.0165 0.0494 1.0000
7.500 0.7206 0.05215 0.04754 0.0177 0.0476 1.0000
7.750 0.7297 0.05817 0.05348 0.0177 0.0460 1.0000
8.000 0.7227 0.06450 0.06006 0.0193 0.0453 1.0000
8.250 0.7199 0.06589 0.06184 0.0217 0.0447 1.0000
8.500 0.7104 0.06830 0.06466 0.0231 0.0426 1.0000
8.750 0.7010 0.07241 0.06891 0.0231 0.0416 1.0000
9.000 0.6871 0.07655 0.07309 0.0227 0.0412 1.0000
9.250 0.6728 0.08181 0.07840 0.0194 0.0411 1.0000
9.500 0.6620 0.08859 0.08518 0.0129 0.0412 1.0000
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Polar data table (+)
Polar graphs
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