AH 79-100 A AIRFOIL (ah79100a-il)
AH 79-100 A AIRFOIL - Althaus AH 79-100A airfoil
| Details | Dat file | Parser | |
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(ah79100a-il) AH 79-100 A AIRFOIL Althaus AH 79-100A airfoil Max thickness 10% at 27.9% chord. Max camber 3.6% at 56.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
AH 79-100 A AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010700 0.0048200
0.0042800 0.0094500
0.0096100 0.0145900
0.0170400 0.0202100
0.0265300 0.0259900
0.0380600 0.0317700
0.0515600 0.0375200
0.0669900 0.0431200
0.0842700 0.0485000
0.1033200 0.0535600
0.1240800 0.0583700
0.1464500 0.0628100
0.1703300 0.0668900
0.1956200 0.0704500
0.2222100 0.0735600
0.2500000 0.0760900
0.2788600 0.0781100
0.3086600 0.0795100
0.3392800 0.0803900
0.3705900 0.0806500
0.4024500 0.0803800
0.4347400 0.0795200
0.4673000 0.0781500
0.5000000 0.0762500
0.5327000 0.0739700
0.5652600 0.0713000
0.5975500 0.0682500
0.6294100 0.0648100
0.6607200 0.0610400
0.6913400 0.0569500
0.7211400 0.0526100
0.7500000 0.0480800
0.7777900 0.0434300
0.8043801 0.0387400
0.8296700 0.0341300
0.8535500 0.0296600
0.8759201 0.0254000
0.8966800 0.0213500
0.9157300 0.0175700
0.9330100 0.0140800
0.9484400 0.0109400
0.9619400 0.0081500
0.9734700 0.0057400
0.9829600 0.0037300
0.9903900 0.0020200
0.9957200 0.0007600
0.9989300 0.0003800
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0036700
0.0042800 -.0071600
0.0096100 -.0104300
0.0170400 -.0132400
0.0265300 -.0158100
0.0380600 -.0180000
0.0515600 -.0199500
0.0669900 -.0215600
0.0842700 -.0229100
0.1033200 -.0239600
0.1240800 -.0247300
0.1464500 -.0251200
0.1703300 -.0252200
0.1956200 -.0249100
0.2222100 -.0243100
0.2500000 -.0232600
0.2788600 -.0218900
0.3086600 -.0200800
0.3392800 -.0179400
0.3705900 -.0154400
0.4024500 -.0127300
0.4347400 -.0098200
0.4673000 -.0068900
0.5000000 -.0039400
0.5327000 -.0011100
0.5652600 0.0016000
0.5975500 0.0040200
0.6294100 0.0061400
0.6607200 0.0078500
0.6913400 0.0092000
0.7211400 0.0101900
0.7500000 0.0108300
0.7777900 0.0111300
0.8043801 0.0111000
0.8296700 0.0107400
0.8535500 0.0101300
0.8759201 0.0092800
0.8966800 0.0082700
0.9157300 0.0071300
0.9330100 0.0059300
0.9484400 0.0047000
0.9619400 0.0035000
0.9734700 0.0023600
0.9829600 0.0013700
0.9903900 0.0006800
0.9957200 0.0001600
0.9989300 0.0000800
1.0000000 0.0000000
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Polars for AH 79-100 A AIRFOIL (ah79100a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79100a-il | 50,000 | 9 | 39.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100a-il | 50,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100a-il | 100,000 | 9 | 61.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100a-il | 100,000 | 5 | 62.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100a-il | 200,000 | 9 | 85.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100a-il | 200,000 | 5 | 81.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100a-il | 500,000 | 9 | 116.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100a-il | 500,000 | 5 | 103.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100a-il | 1,000,000 | 9 | 137 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100a-il | 1,000,000 | 5 | 107.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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