RG 8 AIRFOIL (rg8-il)
RG 8 AIRFOIL - Rolf Girsberger RG 8 airfoil
| Details | Dat file | Parser | |
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(rg8-il) RG 8 AIRFOIL Rolf Girsberger RG 8 airfoil Max thickness 10.8% at 31.1% chord. Max camber 2.2% at 60.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RG 8 AIRFOIL
32. 30.
0.0000000 0.0000000
0.0036000 0.0077900
0.0116900 0.0157700
0.0242100 0.0240500
0.0410500 0.0323000
0.0621100 0.0402300
0.0872400 0.0476300
0.1162700 0.0543100
0.1489800 0.0601300
0.1851200 0.0649800
0.2244000 0.0687800
0.2664900 0.0714900
0.3110300 0.0730900
0.3576000 0.0735900
0.4057700 0.0730300
0.4550800 0.0714600
0.5050400 0.0689500
0.5551600 0.0655800
0.6049200 0.0614700
0.6538100 0.0567200
0.7013100 0.0514700
0.7468900 0.0458600
0.7900701 0.0400100
0.8303300 0.0340700
0.8672200 0.0281900
0.9002800 0.0225000
0.9290799 0.0171200
0.9532100 0.0121100
0.9725300 0.0074000
0.9871399 0.0033800
0.9966400 0.0008200
1.0000000 0.0000000
0.0000000 0.0000000
0.0021900 -.0052100
0.0102400 -.0109700
0.0232800 -.0164500
0.0412400 -.0213700
0.0639800 -.0255900
0.0913600 -.0290300
0.1231800 -.0317000
0.1591400 -.0336300
0.1988400 -.0348400
0.2418500 -.0353800
0.2876900 -.0352500
0.3358000 -.0344600
0.3856200 -.0329900
0.4365500 -.0306900
0.4882500 -.0272800
0.5407100 -.0228700
0.5936100 -.0180200
0.6462600 -.0131700
0.6979200 -.0086200
0.7478400 -.0046300
0.7952400 -.0013800
0.8393400 0.0010200
0.8794000 0.0025200
0.9146900 0.0031500
0.9445600 0.0030200
0.9684500 0.0023300
0.9858600 0.0013300
0.9964499 0.0004000
1.0000000 0.0000000
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Polars for RG 8 AIRFOIL (rg8-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg8-il | 50,000 | 9 | 35.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 50,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 100,000 | 9 | 54.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 100,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 200,000 | 9 | 73.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 200,000 | 5 | 68.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 500,000 | 9 | 96.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 500,000 | 5 | 83.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 1,000,000 | 9 | 107.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 1,000,000 | 5 | 92.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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