AH 79-100 B AIRFOIL (ah79100b-il)
AH 79-100 B AIRFOIL - Althaus AH 79-100B airfoil
| Details | Dat file | Parser | |
|
(ah79100b-il) AH 79-100 B AIRFOIL Althaus AH 79-100B airfoil Max thickness 10% at 30.9% chord. Max camber 6.4% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
AH 79-100 B AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010700 0.0054400
0.0042800 0.0106400
0.0096100 0.0168300
0.0170400 0.0234600
0.0265300 0.0304800
0.0380600 0.0374100
0.0515600 0.0446300
0.0669900 0.0520400
0.0842700 0.0594400
0.1033200 0.0665200
0.1240800 0.0734200
0.1464500 0.0797900
0.1703300 0.0858300
0.1956200 0.0912100
0.2222100 0.0961400
0.2500000 0.1003100
0.2788600 0.1038600
0.3086600 0.1065200
0.3392800 0.1085200
0.3705900 0.1096400
0.4024500 0.1101500
0.4347400 0.1098000
0.4673000 0.1087900
0.5000000 0.1069200
0.5327000 0.1044000
0.5652600 0.1010500
0.5975500 0.0970900
0.6294100 0.0923800
0.6607200 0.0872100
0.6913400 0.0815500
0.7211400 0.0756500
0.7500000 0.0695200
0.7777900 0.0634400
0.8043801 0.0573300
0.8296700 0.0513800
0.8535500 0.0454800
0.8759201 0.0398500
0.8966800 0.0343700
0.9157300 0.0292300
0.9330100 0.0242800
0.9484400 0.0196800
0.9619400 0.0152900
0.9734700 0.0112900
0.9829600 0.0076300
0.9903900 0.0044400
0.9957200 0.0019600
0.9989300 0.0003100
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0032400
0.0042800 -.0062400
0.0096100 -.0087400
0.0170400 -.0101500
0.0265300 -.0107900
0.0380600 -.0108700
0.0515600 -.0105900
0.0669900 -.0099500
0.0842700 -.0090400
0.1033200 -.0079300
0.1240800 -.0066800
0.1464500 -.0052400
0.1703300 -.0037000
0.1956200 -.0019800
0.2222100 -.0001500
0.2500000 0.0018500
0.2788600 0.0039100
0.3086600 0.0061500
0.3392800 0.0084700
0.3705900 0.0109900
0.4024500 0.0135600
0.4347400 0.0162200
0.4673000 0.0188500
0.5000000 0.0214700
0.5327000 0.0239100
0.5652600 0.0261000
0.5975500 0.0279000
0.6294100 0.0293600
0.6607200 0.0303700
0.6913400 0.0309900
0.7211400 0.0311700
0.7500000 0.0309700
0.7777900 0.0303600
0.8043801 0.0293700
0.8296700 0.0279700
0.8535500 0.0261900
0.8759201 0.0240700
0.8966800 0.0216900
0.9157300 0.0191100
0.9330100 0.0163900
0.9484400 0.0135700
0.9619400 0.0107100
0.9734700 0.0079000
0.9829600 0.0052700
0.9903900 0.0031000
0.9957200 0.0013600
0.9989300 0.0001600
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AH 79-100 B AIRFOIL (ah79100b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah79100b-il | 50,000 | 9 | 32.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 50,000 | 5 | 32.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 9 | 65.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 5 | 68.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 9 | 100 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 5 | 101 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 9 | 148.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 5 | 139.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 9 | 183.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 5 | 153.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||