HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)
HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) - Airfoil measured from an ASW22 wing
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(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord. Max camber 4.5% at 42% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED)
48. 48.
0.000000 0.000000
0.002350 0.006570
0.007040 0.014080
0.016420 0.023460
0.025810 0.031300
0.035190 0.037540
0.044580 0.043170
0.053970 0.047860
0.063350 0.052560
0.082120 0.061000
0.100890 0.068510
0.129050 0.077900
0.157200 0.086200
0.185360 0.093300
0.213510 0.099200
0.241670 0.104300
0.269830 0.108870
0.297980 0.112620
0.326140 0.115440
0.349600 0.117600
0.373060 0.119190
0.396530 0.120500
0.419990 0.121200
0.443450 0.121200
0.466920 0.121000
0.490380 0.120300
0.513840 0.119100
0.537310 0.117320
0.560770 0.114900
0.584230 0.112000
0.607700 0.108870
0.631160 0.105110
0.654620 0.100420
0.678090 0.095730
0.701550 0.090100
0.725010 0.084500
0.748470 0.077900
0.771940 0.071330
0.795400 0.063820
0.818860 0.056310
0.842330 0.048500
0.865790 0.041300
0.889250 0.033500
0.912720 0.025700
0.936180 0.018770
0.959640 0.011500
0.983110 0.004690
1.000000 0.000000
0.000000 0.000000
0.002350 -.004690
0.007040 -.008450
0.016420 -.011800
0.025810 -.014080
0.035190 -.015950
0.044580 -.017500
0.053970 -.018900
0.063350 -.020200
0.082120 -.022100
0.100890 -.023600
0.129050 -.025200
0.157200 -.026400
0.185360 -.027400
0.213510 -.028200
0.241670 -.029000
0.269830 -.029700
0.297980 -.030200
0.326140 -.030700
0.349600 -.030900
0.373060 -.030900
0.396530 -.030970
0.419990 -.030970
0.443450 -.030970
0.466920 -.030900
0.490380 -.030600
0.513840 -.030030
0.537310 -.029300
0.560770 -.028500
0.584230 -.027500
0.607700 -.026400
0.631160 -.025000
0.654620 -.023600
0.678090 -.021800
0.701550 -.019800
0.725010 -.017500
0.748470 -.014800
0.771940 -.011500
0.795400 -.008450
0.818860 -.004690
0.842330 -.001400
0.865790 0.001880
0.889250 0.003750
0.912720 0.004200
0.936180 0.003700
0.959640 0.002500
0.983110 0.001000
1.000000 0.000000
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Polars for HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq17-il | 50,000 | 9 | 22.5 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 50,000 | 5 | 18.3 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 100,000 | 9 | 34.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 100,000 | 5 | 32.5 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 200,000 | 9 | 68.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 200,000 | 5 | 66.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 500,000 | 9 | 113.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 500,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 1,000,000 | 9 | 139.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 1,000,000 | 5 | 122.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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