HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 200,000 Max Cl/Cd: 84.54 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1404-il-200000.txt Download as CSV file: xf-hs1404-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-404 AIRFOIL
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 -0.4796 0.12046 0.11680 -0.0065 1.0000 0.0183
-9.000 -0.4733 0.11709 0.11345 -0.0082 1.0000 0.0183
-8.750 -0.4718 0.10972 0.10613 -0.0073 1.0000 0.0193
-8.500 -0.4639 0.10572 0.10214 -0.0068 1.0000 0.0202
-8.250 -0.4575 0.10242 0.09887 -0.0076 1.0000 0.0209
-8.000 -0.4515 0.09924 0.09571 -0.0087 1.0000 0.0216
-7.750 -0.4459 0.09612 0.09262 -0.0100 1.0000 0.0224
-7.500 -0.4408 0.09306 0.08960 -0.0113 1.0000 0.0231
-7.250 -0.4356 0.09000 0.08658 -0.0129 1.0000 0.0239
-7.000 -0.4270 0.08663 0.08325 -0.0156 1.0000 0.0249
-6.750 -0.4169 0.08315 0.07979 -0.0189 1.0000 0.0260
-6.500 -0.4048 0.07956 0.07616 -0.0227 1.0000 0.0273
-6.250 -0.3876 0.07595 0.07256 -0.0287 1.0000 0.0288
-6.000 -0.3613 0.07234 0.06892 -0.0373 1.0000 0.0299
-5.750 -0.3396 0.06858 0.06512 -0.0422 1.0000 0.0301
-5.500 -0.3189 0.06459 0.06106 -0.0460 1.0000 0.0303
-5.250 -0.3202 0.05876 0.05532 -0.0452 1.0000 0.0318
-5.000 -0.3101 0.05600 0.05258 -0.0445 1.0000 0.0335
-4.750 -0.2930 0.05279 0.04932 -0.0462 1.0000 0.0358
-4.500 -0.2687 0.04897 0.04540 -0.0496 1.0000 0.0393
-4.250 -0.2231 0.04300 0.03897 -0.0578 1.0000 0.0435
-4.000 -0.2112 0.03976 0.03581 -0.0573 1.0000 0.0455
-3.750 -0.1906 0.03741 0.03338 -0.0578 1.0000 0.0513
-2.750 -0.0456 0.02009 0.01380 -0.0663 1.0000 0.0305
-2.500 -0.0076 0.01662 0.00980 -0.0683 1.0000 0.0271
-2.250 0.0275 0.01481 0.00764 -0.0693 1.0000 0.0254
-2.000 0.0606 0.01359 0.00618 -0.0701 1.0000 0.0252
-1.750 0.0923 0.01279 0.00525 -0.0708 1.0000 0.0266
-1.500 0.1241 0.01216 0.00449 -0.0714 1.0000 0.0368
-1.250 0.1544 0.01166 0.00468 -0.0725 1.0000 0.2303
-1.000 0.1807 0.01162 0.00470 -0.0727 1.0000 0.2725
-0.750 0.2132 0.01139 0.00462 -0.0742 0.9986 0.3210
-0.500 0.2437 0.00961 0.00447 -0.0747 0.9964 1.0000
-0.250 0.2825 0.00974 0.00440 -0.0772 0.9918 1.0000
0.000 0.3239 0.00982 0.00434 -0.0802 0.9856 1.0000
0.250 0.3675 0.00982 0.00425 -0.0836 0.9777 1.0000
0.500 0.4130 0.00975 0.00415 -0.0873 0.9707 1.0000
0.750 0.4494 0.00976 0.00417 -0.0891 0.9629 1.0000
1.000 0.4905 0.00972 0.00414 -0.0920 0.9581 1.0000
1.250 0.5257 0.00972 0.00417 -0.0935 0.9507 1.0000
1.500 0.5640 0.00963 0.00414 -0.0955 0.9444 1.0000
1.750 0.5960 0.00959 0.00418 -0.0961 0.9347 1.0000
2.000 0.6280 0.00950 0.00418 -0.0965 0.9246 1.0000
2.250 0.6572 0.00925 0.00410 -0.0956 0.9074 1.0000
2.500 0.6805 0.00895 0.00382 -0.0931 0.8797 1.0000
2.750 0.7019 0.00880 0.00367 -0.0903 0.8456 1.0000
3.000 0.7240 0.00876 0.00360 -0.0880 0.8040 1.0000
3.250 0.7465 0.00883 0.00361 -0.0859 0.7487 1.0000
3.500 0.7659 0.00926 0.00356 -0.0831 0.6084 1.0000
3.750 0.7757 0.01156 0.00420 -0.0799 0.3015 1.0000
4.000 0.7896 0.01444 0.00581 -0.0782 0.0724 1.0000
4.250 0.8123 0.01568 0.00711 -0.0771 0.0572 1.0000
4.500 0.8343 0.01715 0.00859 -0.0759 0.0484 1.0000
4.750 0.8582 0.01834 0.00991 -0.0749 0.0408 1.0000
5.000 0.8804 0.02150 0.01307 -0.0736 0.0344 1.0000
5.250 0.9050 0.02247 0.01423 -0.0727 0.0238 1.0000
5.500 0.9302 0.02444 0.01657 -0.0714 0.0172 1.0000
5.750 0.9509 0.02716 0.01955 -0.0704 0.0124 1.0000
6.000 0.9691 0.03286 0.02594 -0.0682 0.0119 1.0000
6.250 0.9868 0.03700 0.03059 -0.0662 0.0120 1.0000
6.500 1.0067 0.03968 0.03362 -0.0645 0.0124 1.0000
6.750 1.0234 0.04665 0.04149 -0.0604 0.0175 1.0000
7.000 1.0327 0.05405 0.04947 -0.0574 0.0274 1.0000
7.250 1.0389 0.05889 0.05464 -0.0557 0.0272 1.0000
7.500 1.0423 0.06360 0.05962 -0.0543 0.0266 1.0000
7.750 1.0427 0.06827 0.06452 -0.0532 0.0261 1.0000
8.000 1.0399 0.07292 0.06936 -0.0522 0.0256 1.0000
8.250 1.0339 0.07755 0.07425 -0.0516 0.0253 1.0000
8.500 1.0237 0.08213 0.07895 -0.0512 0.0251 1.0000
8.750 1.0079 0.08673 0.08357 -0.0513 0.0251 1.0000
9.000 0.9918 0.09257 0.08951 -0.0543 0.0252 1.0000
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Polar data table (+)
Polar graphs
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