K3311 (original) (k3311-il)
K3311 (original) - Leon Kincaid K3311 airfoil (original)
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(k3311-il) K3311 (original) Leon Kincaid K3311 airfoil (original) Max thickness 11% at 30% chord. Max camber 3.3% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
K3311 (original) 1.0000000 0.0000000 0.9500000 0.0104300 0.9000000 0.0200900 0.8500000 0.0293100 0.8000000 0.0384200 0.7500000 0.0467000 0.7000000 0.0547600 0.6500000 0.0617000 0.6000000 0.0689500 0.5500000 0.0748500 0.5000000 0.0796600 0.4500000 0.0834700 0.4000000 0.0861800 0.3500000 0.0870200 0.3000000 0.0859500 0.2500000 0.0831000 0.2000000 0.0777600 0.1500000 0.0696600 0.1000000 0.0574800 0.0800000 0.0513000 0.0600000 0.0441200 0.0400000 0.0349800 0.0200000 0.0232700 0.0100000 0.0156300 0.0000000 0.0000000 0.0100000 -0.0103600 0.0200000 -0.0128500 0.0400000 -0.0163500 0.0600000 -0.0189600 0.0800000 -0.0204500 0.1000000 -0.0216900 0.1500000 -0.0238700 0.2000000 -0.0249200 0.2500000 -0.0246800 0.3000000 -0.0240500 0.3500000 -0.0226000 0.4000000 -0.0211300 0.4500000 -0.0188300 0.5000000 -0.0160800 0.5500000 -0.0132700 0.6000000 -0.0105300 0.6500000 -0.0081200 0.7000000 -0.0059200 0.7500000 -0.0039600 0.8000000 -0.0023200 0.8500000 -0.0012100 0.9000000 -0.0005100 0.9500000 -0.0005400 1.0000000 0.0000000 |
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Polars for K3311 (original) (k3311-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| k3311-il | 50,000 | 9 | 34.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 100,000 | 9 | 55.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 100,000 | 5 | 56.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 200,000 | 9 | 77.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 500,000 | 9 | 107.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 500,000 | 5 | 100.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 1,000,000 | 9 | 129.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 1,000,000 | 5 | 116.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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