HQ 1.0/10 AIRFOIL (hq1010-il)
HQ 1.0/10 AIRFOIL - Quabeck HQ 1.0/10 R/C sailplane airfoil
| Details | Dat file | Parser | |
|
(hq1010-il) HQ 1.0/10 AIRFOIL Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord. Max camber 1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
HQ 1.0/10 AIRFOIL
39. 39.
0.0000000 0.0000000
0.0025000 0.0057000
0.0050000 0.0085700
0.0087500 0.0118000
0.0125000 0.0144500
0.0187500 0.0181800
0.0250000 0.0212800
0.0375000 0.0264000
0.0500000 0.0305500
0.0750000 0.0371900
0.1000000 0.0423200
0.1250000 0.0464100
0.1500000 0.0496600
0.1750000 0.0521800
0.2000000 0.0541100
0.2250000 0.0556200
0.2500000 0.0568500
0.2750000 0.0578700
0.3000000 0.0586700
0.3250000 0.0591900
0.3500000 0.0594000
0.3750000 0.0593200
0.4000000 0.0589700
0.4500000 0.0575800
0.5000000 0.0552200
0.5500000 0.0518700
0.6000000 0.0476000
0.6500000 0.0425200
0.7000000 0.0368800
0.7500000 0.0307300
0.8000000 0.0243000
0.8250000 0.0210300
0.8500000 0.0178300
0.8750000 0.0147300
0.9000000 0.0116700
0.9250000 0.0087300
0.9500000 0.0056700
0.9750000 0.0026900
1.0000000 0.0000000
0.0000000 0.0000000
0.0025000 -.0046000
0.0050000 -.0068100
0.0087500 -.0093700
0.0125000 -.0114300
0.0187500 -.0142500
0.0250000 -.0164500
0.0375000 -.0199700
0.0500000 -.0227200
0.0750000 -.0270200
0.1000000 -.0302800
0.1250000 -.0328600
0.1500000 -.0348900
0.1750000 -.0364500
0.2000000 -.0376200
0.2250000 -.0385100
0.2500000 -.0391900
0.2750000 -.0397300
0.3000000 -.0401100
0.3250000 -.0402800
0.3500000 -.0402000
0.3750000 -.0398700
0.4000000 -.0393300
0.4500000 -.0376600
0.5000000 -.0352300
0.5500000 -.0320400
0.6000000 -.0281800
0.6500000 -.0238400
0.7000000 -.0193000
0.7500000 -.0147200
0.8000000 -.0104000
0.8250000 -.0084300
0.8500000 -.0066600
0.8750000 -.0051500
0.9000000 -.0038000
0.9250000 -.0027200
0.9500000 -.0015800
0.9750000 -.0006500
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 HQ 1.0/10 AIRFOIL (hq1010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq1010-il | 50,000 | 9 | 32.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 5 | 45.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 9 | 63.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 5 | 55.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 9 | 79.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 5 | 68.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 9 | 85.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 5 | 78 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||