AH 93-156 (ah93156-il)
AH 93-156 - Althaus AH 93-156 airfoil
| Details | Dat file | Parser | |
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(ah93156-il) AH 93-156 Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord. Max camber 3.7% at 41.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 93-156 1.00000 -0.00197 0.99157 0.00025 0.97915 0.00318 0.96383 0.00651 0.94756 0.01005 0.92961 0.01406 0.91066 0.01849 0.89176 0.02317 0.87275 0.02810 0.85372 0.03325 0.83461 0.03858 0.81541 0.04407 0.79612 0.04968 0.77675 0.05534 0.75742 0.06097 0.73820 0.06649 0.71907 0.07188 0.70005 0.07707 0.68112 0.08202 0.66228 0.08669 0.64352 0.09103 0.62477 0.09501 0.60601 0.09862 0.58720 0.10186 0.56832 0.10474 0.54936 0.10726 0.53032 0.10943 0.51120 0.11126 0.49202 0.11276 0.47277 0.11394 0.45347 0.11482 0.43413 0.11540 0.41477 0.11568 0.39540 0.11568 0.37603 0.11540 0.35670 0.11482 0.33743 0.11394 0.31822 0.11274 0.29909 0.11122 0.28004 0.10935 0.26108 0.10712 0.24222 0.10452 0.22346 0.10155 0.20483 0.09818 0.18636 0.09441 0.16809 0.09022 0.15005 0.08559 0.13231 0.08050 0.11493 0.07492 0.09797 0.06883 0.08153 0.06221 0.06578 0.05506 0.05097 0.04742 0.03753 0.03949 0.02609 0.03166 0.01716 0.02450 0.01073 0.01837 0.00628 0.01327 0.00326 0.00898 0.00129 0.00526 0.00019 0.00196 0.00006 -0.00113 0.00086 -0.00422 0.00268 -0.00735 0.00561 -0.01038 0.00979 -0.01333 0.01556 -0.01627 0.02354 -0.01927 0.03443 -0.02233 0.04846 -0.02529 0.06493 -0.02795 0.08286 -0.03022 0.10159 -0.03211 0.12077 -0.03369 0.14022 -0.03502 0.15985 -0.03615 0.17961 -0.03711 0.19946 -0.03792 0.21936 -0.03861 0.23932 -0.03919 0.25931 -0.03967 0.27933 -0.04006 0.29938 -0.04037 0.31945 -0.04061 0.33955 -0.04078 0.35967 -0.04089 0.37980 -0.04095 0.39994 -0.04095 0.42009 -0.04092 0.44024 -0.04083 0.46039 -0.04070 0.48054 -0.04053 0.50066 -0.04030 0.52077 -0.04002 0.54085 -0.03968 0.56091 -0.03927 0.58094 -0.03878 0.60094 -0.03820 0.62090 -0.03753 0.64081 -0.03675 0.66067 -0.03585 0.68048 -0.03481 0.70021 -0.03362 0.71987 -0.03226 0.73941 -0.03071 0.75882 -0.02893 0.77805 -0.02690 0.79710 -0.02456 0.81603 -0.02187 0.83496 -0.01880 0.85409 -0.01538 0.87330 -0.01180 0.89212 -0.00847 0.91039 -0.00570 0.92825 -0.00360 0.94574 -0.00226 0.96269 -0.00172 0.97854 -0.00183 0.99127 -0.00201 1.00000 -0.00197 |
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Polars for AH 93-156 (ah93156-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93156-il | 50,000 | 9 | 4.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 50,000 | 5 | 15.6 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 100,000 | 9 | 39 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 100,000 | 5 | 35.5 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 200,000 | 9 | 72.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 200,000 | 5 | 64.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 500,000 | 5 | 94.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 1,000,000 | 9 | 125 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 1,000,000 | 5 | 114.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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