HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il) Reynolds number: 100,000 Max Cl/Cd: 28.74 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1430-il-100000.txt Download as CSV file: xf-hs1430-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-430 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6238 0.09978 0.09302 -0.0588 0.9547 0.2285
-10.250 -0.7812 0.08627 0.07902 -0.0471 0.9489 0.2275
-10.000 -0.8705 0.08096 0.07339 -0.0337 0.9396 0.2275
-9.750 -0.9301 0.07588 0.06783 -0.0239 0.9330 0.2287
-9.500 -0.9389 0.07240 0.06414 -0.0203 0.9267 0.2306
-9.250 -0.9003 0.07184 0.06375 -0.0228 0.9211 0.2330
-9.000 -0.8691 0.07130 0.06330 -0.0242 0.9157 0.2357
-8.750 -0.8625 0.06991 0.06183 -0.0220 0.9099 0.2381
-8.500 -0.8595 0.06794 0.05968 -0.0194 0.9047 0.2409
-8.250 -0.8651 0.06602 0.05751 -0.0153 0.8986 0.2433
-8.000 -0.8604 0.06390 0.05506 -0.0127 0.8934 0.2461
-7.750 -0.8623 0.06257 0.05339 -0.0086 0.8866 0.2483
-7.500 -0.8431 0.06053 0.05134 -0.0085 0.8822 0.2510
-7.250 -0.8076 0.05961 0.05049 -0.0107 0.8793 0.2543
-7.000 -0.8013 0.05920 0.05009 -0.0076 0.8716 0.2565
-6.750 -0.7721 0.05827 0.04909 -0.0086 0.8671 0.2598
-6.500 -0.7468 0.05730 0.04798 -0.0088 0.8629 0.2633
-6.250 -0.7416 0.05672 0.04725 -0.0056 0.8550 0.2660
-6.000 -0.7114 0.05580 0.04605 -0.0065 0.8510 0.2695
-5.750 -0.6980 0.05470 0.04485 -0.0048 0.8442 0.2721
-5.500 -0.6733 0.05376 0.04397 -0.0050 0.8378 0.2754
-5.250 -0.6328 0.05287 0.04310 -0.0076 0.8341 0.2795
-5.000 -0.6181 0.05265 0.04286 -0.0059 0.8269 0.2827
-4.750 -0.5957 0.05217 0.04231 -0.0054 0.8199 0.2862
-4.500 -0.5550 0.05123 0.04122 -0.0077 0.8159 0.2907
-4.250 -0.5358 0.05102 0.04087 -0.0066 0.8086 0.2938
-4.000 -0.5157 0.05029 0.04009 -0.0058 0.8007 0.2972
-3.750 -0.4713 0.04902 0.03890 -0.0089 0.7966 0.3020
-3.500 -0.4199 0.04777 0.03767 -0.0128 0.7937 0.3075
-3.250 -0.4249 0.04841 0.03831 -0.0079 0.7806 0.3102
-3.000 -0.3850 0.04756 0.03738 -0.0099 0.7759 0.3158
-2.750 -0.3375 0.04649 0.03618 -0.0130 0.7729 0.3211
-2.500 -0.3312 0.04663 0.03637 -0.0100 0.7612 0.3247
-2.250 -0.2936 0.04562 0.03548 -0.0115 0.7545 0.3308
-2.000 -0.2413 0.04408 0.03399 -0.0151 0.7510 0.3387
-1.750 -0.1857 0.04233 0.03216 -0.0191 0.7485 0.3470
-1.500 -0.1880 0.04312 0.03296 -0.0145 0.7330 0.3506
-1.250 -0.1425 0.04166 0.03170 -0.0171 0.7289 0.3594
-1.000 -0.0954 0.04027 0.03036 -0.0198 0.7261 0.3693
-0.750 -0.0441 0.03864 0.02873 -0.0232 0.7243 0.3796
-0.500 -0.0395 0.03926 0.02953 -0.0196 0.7113 0.3863
-0.250 -0.0041 0.03825 0.02863 -0.0204 0.7049 0.3985
0.000 0.0461 0.03646 0.02701 -0.0235 0.7019 0.4155
0.250 0.1024 0.03437 0.02514 -0.0275 0.6996 0.4423
0.500 0.1617 0.03185 0.02321 -0.0321 0.6974 0.5059
0.750 0.2276 0.02944 0.02182 -0.0368 0.6949 0.7114
1.000 0.2014 0.03121 0.02389 -0.0265 0.6759 0.7540
1.250 0.3094 0.03007 0.02281 -0.0381 0.6708 0.8314
1.500 0.3232 0.03119 0.02398 -0.0345 0.6544 0.8559
1.750 0.4406 0.03072 0.02323 -0.0489 0.6407 0.8771
2.000 0.4692 0.03174 0.02422 -0.0481 0.6176 0.8894
2.250 0.4867 0.03231 0.02469 -0.0454 0.5929 0.9063
2.500 0.5317 0.03323 0.02542 -0.0482 0.5534 0.9131
2.750 0.5528 0.03367 0.02549 -0.0466 0.5162 0.9281
3.000 0.5984 0.03468 0.02605 -0.0501 0.4744 0.9335
3.250 0.6411 0.03565 0.02663 -0.0533 0.4477 0.9426
3.500 0.6890 0.03660 0.02730 -0.0576 0.4295 0.9530
3.750 0.7555 0.03734 0.02767 -0.0655 0.4158 0.9613
4.000 0.8037 0.03803 0.02828 -0.0701 0.4061 0.9717
4.250 0.8638 0.03838 0.02842 -0.0771 0.3978 0.9784
4.500 0.9218 0.03876 0.02857 -0.0838 0.3913 0.9868
4.750 0.9718 0.03900 0.02880 -0.0891 0.3856 0.9929
5.000 1.0276 0.03928 0.02899 -0.0955 0.3804 0.9997
5.250 1.0457 0.03937 0.02899 -0.0948 0.3773 1.0000
5.500 1.0653 0.03944 0.02894 -0.0943 0.3744 1.0000
5.750 1.1028 0.03952 0.02881 -0.0972 0.3711 1.0000
6.000 1.1068 0.03976 0.02908 -0.0938 0.3691 1.0000
6.250 1.1118 0.04001 0.02937 -0.0905 0.3671 1.0000
6.500 1.1181 0.04029 0.02968 -0.0874 0.3651 1.0000
6.750 1.1255 0.04060 0.03000 -0.0845 0.3631 1.0000
7.000 1.1340 0.04095 0.03035 -0.0818 0.3612 1.0000
7.250 1.1446 0.04132 0.03071 -0.0794 0.3592 1.0000
7.500 1.1574 0.04172 0.03108 -0.0774 0.3572 1.0000
7.750 1.1741 0.04212 0.03143 -0.0761 0.3550 1.0000
8.000 1.2004 0.04251 0.03171 -0.0765 0.3525 1.0000
8.250 1.2395 0.04313 0.03217 -0.0795 0.3495 1.0000
8.500 1.2306 0.04384 0.03300 -0.0734 0.3481 1.0000
8.750 1.2241 0.04464 0.03392 -0.0679 0.3465 1.0000
9.000 1.2177 0.04555 0.03493 -0.0625 0.3447 1.0000
9.250 1.2117 0.04653 0.03601 -0.0573 0.3428 1.0000
9.500 1.2072 0.04754 0.03710 -0.0525 0.3406 1.0000
9.750 1.2071 0.04851 0.03813 -0.0484 0.3384 1.0000
10.000 1.2158 0.04932 0.03893 -0.0459 0.3358 1.0000
10.250 1.2405 0.04984 0.03936 -0.0459 0.3331 1.0000
10.500 1.2991 0.05036 0.03963 -0.0518 0.3297 1.0000
10.750 1.2622 0.05209 0.04160 -0.0419 0.3282 1.0000
11.000 1.2237 0.05428 0.04404 -0.0325 0.3264 1.0000
11.250 1.1811 0.05704 0.04704 -0.0233 0.3242 1.0000
11.500 1.1349 0.06048 0.05071 -0.0146 0.3218 1.0000
11.750 1.0895 0.06446 0.05491 -0.0069 0.3191 1.0000
12.000 1.0708 0.06735 0.05789 -0.0026 0.3162 1.0000
12.250 1.1317 0.06572 0.05603 -0.0062 0.3133 1.0000
12.500 1.1762 0.06580 0.05596 -0.0085 0.3105 1.0000
12.750 0.3331 0.16893 0.16118 0.0047 0.3370 1.0000
13.000 0.3538 0.17075 0.16297 0.0044 0.3337 1.0000
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Polar data table (+)
Polar graphs
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