AH 94-156 (ah94156-il)
AH 94-156 - Althaus AH 94-156 airfoil
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(ah94156-il) AH 94-156 Althaus AH 94-156 airfoil Max thickness 15.6% at 39.6% chord. Max camber 3.6% at 41.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 94-156 1.00000 0.00037 0.99137 0.00186 0.97931 0.00426 0.96327 0.00776 0.94505 0.01180 0.92619 0.01617 0.90722 0.02073 0.88826 0.02547 0.86931 0.03036 0.85035 0.03542 0.83137 0.04062 0.81233 0.04595 0.79321 0.05138 0.77404 0.05684 0.75493 0.06226 0.73591 0.06758 0.71697 0.07276 0.69811 0.07775 0.67934 0.08251 0.66063 0.08700 0.64197 0.09118 0.62332 0.09502 0.60465 0.09851 0.58593 0.10164 0.56716 0.10442 0.54832 0.10686 0.52941 0.10895 0.51043 0.11071 0.49139 0.11216 0.47230 0.11329 0.45317 0.11413 0.43400 0.11467 0.41481 0.11493 0.39561 0.11490 0.37643 0.11460 0.35726 0.11400 0.33815 0.11311 0.31910 0.11191 0.30011 0.11040 0.28120 0.10854 0.26237 0.10634 0.24364 0.10378 0.22500 0.10084 0.20649 0.09753 0.18812 0.09381 0.16993 0.08969 0.15195 0.08513 0.13425 0.08012 0.11686 0.07463 0.09986 0.06863 0.08330 0.06208 0.06734 0.05501 0.05224 0.04747 0.03849 0.03962 0.02674 0.03185 0.01755 0.02471 0.01093 0.01857 0.00636 0.01345 0.00326 0.00912 0.00125 0.00536 0.00019 0.00199 0.00006 -0.00109 0.00100 -0.00417 0.00319 -0.00710 0.00661 -0.00975 0.01141 -0.01229 0.01806 -0.01492 0.02735 -0.01775 0.03996 -0.02076 0.05558 -0.02374 0.07305 -0.02643 0.09141 -0.02876 0.11023 -0.03075 0.12934 -0.03247 0.14864 -0.03395 0.16807 -0.03523 0.18759 -0.03635 0.20717 -0.03732 0.22681 -0.03816 0.24649 -0.03887 0.26620 -0.03947 0.28593 -0.03997 0.30569 -0.04038 0.32546 -0.04070 0.34524 -0.04093 0.36504 -0.04108 0.38484 -0.04115 0.40465 -0.04115 0.42446 -0.04107 0.44428 -0.04091 0.46409 -0.04069 0.48390 -0.04039 0.50371 -0.04001 0.52352 -0.03957 0.54331 -0.03904 0.56309 -0.03844 0.58286 -0.03775 0.60261 -0.03698 0.62234 -0.03611 0.64204 -0.03514 0.66170 -0.03407 0.68130 -0.03287 0.70084 -0.03154 0.72027 -0.03005 0.73953 -0.02837 0.75854 -0.02646 0.77719 -0.02423 0.79560 -0.02152 0.81419 -0.01827 0.83326 -0.01465 0.85241 -0.01102 0.87125 -0.00767 0.88977 -0.00474 0.90798 -0.00234 0.92591 -0.00058 0.94364 0.00045 0.96127 0.00075 0.97789 0.00062 0.99101 0.00045 1.00000 0.00037 |
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Polars for AH 94-156 (ah94156-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah94156-il | 50,000 | 9 | 6.3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94156-il | 50,000 | 5 | 16.7 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94156-il | 100,000 | 9 | 40.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94156-il | 100,000 | 5 | 36.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94156-il | 200,000 | 9 | 72.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94156-il | 200,000 | 5 | 64.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94156-il | 500,000 | 9 | 103.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94156-il | 500,000 | 5 | 95.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94156-il | 1,000,000 | 9 | 125.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94156-il | 1,000,000 | 5 | 115.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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