HQ 0/9 AIRFOIL (hq09-il)
HQ 0/9 AIRFOIL - Quabeck HQ 0/9 R/C sailplane airfoil
| Details | Dat file | Parser | |
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(hq09-il) HQ 0/9 AIRFOIL Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
HQ 0/9 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0011100 0.0026500
0.0043300 0.0061300
0.0095600 0.0094600
0.0170000 0.0127400
0.0265600 0.0159600
0.0381100 0.0190400
0.0515600 0.0219500
0.0670000 0.0247100
0.0842200 0.0273200
0.1033300 0.0298000
0.1241100 0.0321400
0.1464400 0.0342300
0.1703300 0.0358900
0.1956700 0.0370400
0.2222200 0.0381000
0.2500000 0.0390500
0.2788900 0.0397600
0.3086700 0.0402700
0.3393300 0.0405600
0.3705600 0.0404100
0.4024400 0.0398400
0.4347800 0.0390400
0.4673300 0.0380700
0.5000000 0.0368300
0.5326700 0.0352400
0.5652200 0.0333100
0.5975600 0.0311000
0.6294400 0.0286700
0.6606700 0.0261000
0.6913300 0.0235000
0.7211100 0.0209300
0.7500000 0.0184300
0.7777800 0.0160100
0.8043300 0.0137000
0.8296700 0.0115500
0.8535600 0.0096200
0.8758900 0.0079500
0.8966700 0.0064600
0.9157800 0.0050800
0.9330000 0.0038500
0.9484400 0.0028100
0.9618900 0.0019900
0.9734400 0.0013500
0.9830000 0.0008600
0.9904400 0.0004800
0.9956700 0.0002100
0.9988900 0.0000500
1.0000000 0.0000000
0.0000000 0.0000000
0.0011100 -.0026500
0.0043300 -.0061300
0.0095600 -.0094600
0.0170000 -.0127400
0.0265600 -.0159600
0.0381100 -.0190400
0.0515600 -.0219500
0.0670000 -.0247100
0.0842200 -.0273200
0.1033300 -.0298000
0.1241100 -.0321400
0.1464400 -.0342300
0.1703300 -.0358900
0.1956700 -.0370400
0.2222200 -.0381000
0.2500000 -.0390500
0.2788900 -.0397600
0.3086700 -.0402700
0.3393300 -.0405600
0.3705600 -.0404100
0.4024400 -.0398400
0.4347800 -.0390400
0.4673300 -.0380700
0.5000000 -.0368300
0.5326700 -.0352400
0.5652200 -.0333100
0.5975600 -.0311000
0.6294400 -.0286700
0.6606700 -.0261000
0.6913300 -.0235000
0.7211100 -.0209300
0.7500000 -.0184300
0.7777800 -.0160100
0.8043300 -.0137000
0.8296700 -.0115500
0.8535600 -.0096200
0.8758900 -.0079500
0.8966700 -.0064600
0.9157800 -.0050800
0.9330000 -.0038500
0.9484400 -.0028100
0.9618900 -.0019900
0.9734400 -.0013500
0.9830000 -.0008600
0.9904400 -.0004800
0.9956700 -.0002100
0.9988900 -.0000500
1.0000000 0.0000000
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Polars for HQ 0/9 AIRFOIL (hq09-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq09-il | 50,000 | 9 | 27.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 50,000 | 5 | 26 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 9 | 36.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 5 | 33.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 9 | 46.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 5 | 38.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 9 | 51.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 5 | 53.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 9 | 64.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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