HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il) Reynolds number: 100,000 Max Cl/Cd: 59.4 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1404-il-100000-n5.txt Download as CSV file: xf-hs1404-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4745 0.11620 0.11108 -0.0065 1.0000 0.0295
-8.750 -0.4706 0.11359 0.10852 -0.0089 1.0000 0.0297
-8.500 -0.4659 0.11072 0.10570 -0.0112 1.0000 0.0299
-8.250 -0.4610 0.10771 0.10274 -0.0133 1.0000 0.0300
-8.000 -0.4558 0.10460 0.09968 -0.0153 1.0000 0.0301
-7.750 -0.4478 0.10115 0.09627 -0.0182 1.0000 0.0301
-7.500 -0.4381 0.09747 0.09263 -0.0214 1.0000 0.0302
-7.250 -0.4272 0.09364 0.08882 -0.0245 1.0000 0.0302
-7.000 -0.4154 0.08969 0.08490 -0.0276 1.0000 0.0302
-6.750 -0.4026 0.08566 0.08089 -0.0307 1.0000 0.0302
-6.250 -0.3748 0.07738 0.07262 -0.0368 1.0000 0.0302
-5.750 -0.3661 0.06975 0.06502 -0.0336 1.0000 0.0351
-5.500 -0.3279 0.05360 0.04935 -0.0322 1.0000 0.0455
-5.250 -0.3207 0.05045 0.04622 -0.0322 1.0000 0.0484
-5.000 -0.3089 0.04657 0.04231 -0.0347 1.0000 0.0487
-4.750 -0.2788 0.05183 0.04682 -0.0502 1.0000 0.0268
-4.500 -0.2522 0.04693 0.04178 -0.0540 1.0000 0.0237
-4.250 -0.2161 0.04048 0.03501 -0.0594 1.0000 0.0207
-3.750 -0.1488 0.03099 0.02458 -0.0649 1.0000 0.0181
-3.500 -0.1176 0.02699 0.02005 -0.0669 1.0000 0.0178
-3.250 -0.0866 0.02379 0.01624 -0.0681 1.0000 0.0176
-3.000 -0.0563 0.02131 0.01320 -0.0688 1.0000 0.0175
-2.750 -0.0267 0.01938 0.01083 -0.0691 1.0000 0.0176
-2.500 0.0024 0.01790 0.00902 -0.0693 1.0000 0.0179
-2.250 0.0317 0.01669 0.00757 -0.0695 1.0000 0.0186
-2.000 0.0614 0.01566 0.00622 -0.0699 1.0000 0.0217
-1.750 0.0905 0.01489 0.00543 -0.0702 1.0000 0.0417
-1.500 0.1186 0.01435 0.00555 -0.0708 1.0000 0.2023
-1.250 0.1467 0.01422 0.00532 -0.0711 0.9989 0.2354
-1.000 0.1816 0.01401 0.00506 -0.0729 0.9953 0.2725
-0.750 0.2160 0.01372 0.00488 -0.0746 0.9916 0.3293
-0.500 0.2424 0.01204 0.00466 -0.0741 0.9866 1.0000
-0.250 0.2798 0.01219 0.00455 -0.0763 0.9815 1.0000
0.000 0.3148 0.01230 0.00450 -0.0779 0.9741 1.0000
0.250 0.3527 0.01241 0.00450 -0.0802 0.9686 1.0000
0.500 0.3862 0.01253 0.00455 -0.0816 0.9610 1.0000
0.750 0.4247 0.01259 0.00462 -0.0838 0.9539 1.0000
1.000 0.4653 0.01253 0.00455 -0.0863 0.9434 1.0000
1.250 0.5015 0.01247 0.00451 -0.0877 0.9307 1.0000
1.500 0.5336 0.01249 0.00459 -0.0884 0.9195 1.0000
1.750 0.5649 0.01255 0.00472 -0.0889 0.9092 1.0000
2.000 0.5962 0.01258 0.00486 -0.0893 0.8984 1.0000
2.250 0.6267 0.01261 0.00515 -0.0895 0.8862 1.0000
2.500 0.6560 0.01264 0.00532 -0.0894 0.8720 1.0000
2.750 0.6847 0.01263 0.00547 -0.0888 0.8542 1.0000
3.000 0.7105 0.01245 0.00538 -0.0870 0.8147 1.0000
3.250 0.7318 0.01232 0.00512 -0.0837 0.7278 1.0000
3.500 0.7505 0.01285 0.00488 -0.0801 0.5428 1.0000
3.750 0.7652 0.01457 0.00544 -0.0776 0.3309 1.0000
4.000 0.7819 0.01661 0.00654 -0.0763 0.1230 1.0000
4.250 0.8029 0.01815 0.00772 -0.0752 0.0697 1.0000
4.500 0.8257 0.01928 0.00893 -0.0743 0.0523 1.0000
4.750 0.8473 0.02069 0.01048 -0.0731 0.0446 1.0000
5.000 0.8690 0.02220 0.01218 -0.0717 0.0390 1.0000
5.250 0.8913 0.02368 0.01379 -0.0707 0.0303 1.0000
5.500 0.9144 0.02580 0.01608 -0.0694 0.0253 1.0000
5.750 0.9380 0.02838 0.01894 -0.0682 0.0197 1.0000
6.000 0.9619 0.03092 0.02189 -0.0669 0.0154 1.0000
6.250 0.9833 0.03403 0.02543 -0.0655 0.0136 1.0000
6.500 1.0006 0.03806 0.02996 -0.0639 0.0126 1.0000
6.750 1.0104 0.04395 0.03646 -0.0617 0.0118 1.0000
7.000 1.0280 0.04679 0.04010 -0.0597 0.0102 1.0000
7.250 1.0385 0.05124 0.04510 -0.0576 0.0089 1.0000
7.500 1.0447 0.05592 0.05022 -0.0558 0.0081 1.0000
7.750 1.0467 0.06081 0.05550 -0.0541 0.0077 1.0000
8.000 1.0444 0.06587 0.06088 -0.0527 0.0076 1.0000
8.250 1.0380 0.07098 0.06626 -0.0517 0.0076 1.0000
8.500 1.0276 0.07603 0.07151 -0.0511 0.0077 1.0000
8.750 1.0123 0.08078 0.07640 -0.0508 0.0078 1.0000
9.000 0.9967 0.08635 0.08207 -0.0527 0.0081 1.0000
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Polar data table (+)
Polar graphs
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