HQ 2.1/9.5 AIRFOIL (hq2195-il)
HQ 2.1/9.5 AIRFOIL - Quabeck HQ 2.1/9.5 R/C sailplane airfoil
| Details | Dat file | Parser | |
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(hq2195-il) HQ 2.1/9.5 AIRFOIL Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord. Max camber 2.1% at 55% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
HQ 2.1/9.5 AIRFOIL
27. 27.
0.0000000 0.0000000
0.0050000 0.0117500
0.0125000 0.0178400
0.0250000 0.0249200
0.0500000 0.0345800
0.1000000 0.0472500
0.1500000 0.0557200
0.2000000 0.0613200
0.2500000 0.0646100
0.3000000 0.0662300
0.3500000 0.0667800
0.4000000 0.0665200
0.4500100 0.0655500
0.5000000 0.0638400
0.5500000 0.0613000
0.6000000 0.0575100
0.6500000 0.0522600
0.7000000 0.0459300
0.7500000 0.0390600
0.8000000 0.0317200
0.8500000 0.0240100
0.9000000 0.0161500
0.9269800 0.0118500
0.9500000 0.0081300
0.9775701 0.0036700
0.9943600 0.0009300
1.0000000 0.0000100
0.0000000 0.0000000
0.0050000 -.0068500
0.0125000 -.0105400
0.0250000 -.0139600
0.0500000 -.0179800
0.1000000 -.0224300
0.1500000 -.0251000
0.2000000 -.0269600
0.2500000 -.0280900
0.3000000 -.0284700
0.3500000 -.0281400
0.4000000 -.0270200
0.4500100 -.0249900
0.5000000 -.0223400
0.5500000 -.0193200
0.6000000 -.0158500
0.6500000 -.0119200
0.7000000 -.0079900
0.7500000 -.0045600
0.8000000 -.0016000
0.8500000 0.0008900
0.9000000 0.0022700
0.9269800 0.0022700
0.9500000 0.0018300
0.9775701 0.0009100
0.9943600 0.0002300
1.0000000 0.0000000
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Polars for HQ 2.1/9.5 AIRFOIL (hq2195-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2195-il | 50,000 | 9 | 37.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 50,000 | 5 | 37.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 5 | 52.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 9 | 74.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 5 | 79 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 9 | 101 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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