AH 79-100 C AIRFOIL (ah79100c-il)
AH 79-100 C AIRFOIL - Althaus AH 79-100C airfoil
| Details | Dat file | Parser | |
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(ah79100c-il) AH 79-100 C AIRFOIL Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord. Max camber 6.7% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
AH 79-100 C AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010700 0.0056500
0.0042800 0.0105800
0.0096100 0.0167600
0.0170400 0.0235700
0.0265300 0.0311100
0.0380600 0.0386500
0.0515600 0.0463300
0.0669900 0.0539200
0.0842700 0.0613800
0.1033200 0.0685100
0.1240800 0.0753700
0.1464500 0.0816900
0.1703300 0.0876000
0.1956200 0.0929700
0.2222100 0.0978100
0.2500000 0.1020300
0.2788600 0.1056900
0.3086600 0.1086600
0.3392800 0.1110200
0.3705900 0.1126800
0.4024500 0.1136800
0.4347400 0.1139900
0.4673000 0.1136000
0.5000000 0.1124900
0.5327000 0.1106200
0.5652600 0.1079700
0.5975500 0.1045600
0.6294100 0.1005000
0.6607200 0.0958200
0.6913400 0.0906600
0.7211400 0.0851200
0.7500000 0.0792900
0.7777900 0.0732500
0.8043801 0.0670500
0.8296700 0.0607800
0.8535500 0.0544600
0.8759201 0.0481600
0.8966800 0.0419300
0.9157300 0.0358300
0.9330100 0.0297600
0.9484400 0.0237400
0.9619400 0.0178300
0.9734700 0.0123900
0.9829600 0.0077300
0.9903900 0.0043000
0.9957200 0.0018400
0.9989300 0.0003800
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0037600
0.0042800 -.0067900
0.0096100 -.0096000
0.0170400 -.0113300
0.0265300 -.0124700
0.0380600 -.0128400
0.0515600 -.0126900
0.0669900 -.0121000
0.0842700 -.0111300
0.1033200 -.0097400
0.1240800 -.0081500
0.1464500 -.0060500
0.1703300 -.0037200
0.1956200 -.0012400
0.2222100 0.0013000
0.2500000 0.0039600
0.2788600 0.0066000
0.3086600 0.0092300
0.3392800 0.0117500
0.3705900 0.0141500
0.4024500 0.0163600
0.4347400 0.0183300
0.4673000 0.0200600
0.5000000 0.0215200
0.5327000 0.0227800
0.5652600 0.0238100
0.5975500 0.0246300
0.6294100 0.0251700
0.6607200 0.0255000
0.6913400 0.0255400
0.7211400 0.0253200
0.7500000 0.0248500
0.7777900 0.0241000
0.8043801 0.0231000
0.8296700 0.0218700
0.8535500 0.0204000
0.8759201 0.0187100
0.8966800 0.0168800
0.9157300 0.0148800
0.9330100 0.0128000
0.9484400 0.0106200
0.9619400 0.0084500
0.9734700 0.0063000
0.9829600 0.0042800
0.9903900 0.0023500
0.9957200 0.0009700
0.9989300 0.0001600
1.0000000 0.0000000
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Polars for AH 79-100 C AIRFOIL (ah79100c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79100c-il | 50,000 | 9 | 32.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 50,000 | 5 | 31.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 100,000 | 9 | 61.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 100,000 | 5 | 61.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 200,000 | 9 | 97.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 200,000 | 5 | 97 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 500,000 | 9 | 147.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 500,000 | 5 | 137.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 1,000,000 | 9 | 183 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 1,000,000 | 5 | 161.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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