Joukowsky 16.00% thick 1.00% camber


Joukowsky 16.00% thick 1.00% camber
Direct link: Joukowsky 16.00% thick 1.00% camber
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord

Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.

Curve fits of basic Javafoil data for Joukowsky 16.00% thick 1.00% camber, smooth airfoils, Mach 0:


Re: 500k | 1M | 3M | 6M

Re = 500k | 1M | 3M | 6M


Lift: Cl = f(α) = -1.403e-04*α3 + -9.764e-05*α2 + 1.250e-01*α + 1.469e-01
Drag: Cd = f(α) = -4.463e-06*α3 + 2.736e-04*α2 + 4.990e-04*α + -3.752e-04
Moment: Cm = f(α) = -1.015e-07*α3 + 2.401e-05*α2 + -7.341e-06*α + -2.929e-02



Re = 1M | 500k | 3M | 6M


Lift: Cl = f(α) = -1.399e-04*α3 + -8.566e-05*α2 + 1.263e-01*α + 1.461e-01
Drag: Cd = f(α) = -3.645e-06*α3 + 2.210e-04*α2 + 4.213e-04*α + -1.918e-04
Moment: Cm = f(α) = -1.141e-07*α3 + 2.041e-05*α2 + 5.235e-06*α + -2.934e-02



Re = 3M | 500k | 1M | 6M


Lift: Cl = f(α) = -1.374e-04*α3 + -7.648e-05*α2 + 1.277e-01*α + 1.452e-01
Drag: Cd = f(α) = -3.262e-06*α3 + 1.605e-04*α2 + 4.291e-04*α + 2.999e-04
Moment: Cm = f(α) = -1.378e-07*α3 + 1.645e-05*α2 + 1.691e-05*α + -2.935e-02



Re = 6M | 500k | 1M | 3M


Lift: Cl = f(α) = -1.363e-04*α3 + -7.666e-05*α2 + 1.283e-01*α + 1.451e-01
Drag: Cd = f(α) = -2.589e-06*α3 + 1.398e-04*α2 + 3.627e-04*α + 4.001e-04
Moment: Cm = f(α) = -1.444e-07*α3 + 1.499e-05*α2 + 2.419e-05*α + -2.939e-02