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NACA0006 (JF, WT, XF, NF)
NACA0008 (JF, XF, NF)
NACA0009 (JF, WT, XF, NF)
NACA0010 (JF, XF, NF)
NACA0012 (JF, WT, CFD, XF, NF)
NACA0013 (JF, XF, NF)
NACA0015 (JF, XF, NF)
NACA0016 (JF, XF, NF)
NACA0017 (JF, XF, NF)
NACA0018 (JF, XF, NF)
NACA0021 (JF, XF, NF)
NACA0024 (JF, XF, NF)
NACA0025 (JF, XF, NF)
NACA0030 (JF, XF, NF)
NACA1408 (JF, WT, XF, NF)
NACA1409 (JF, XF, NF)
NACA1410 (JF, WT, XF, NF)
NACA1412 (JF, WT, XF, NF)
NACA1415 (JF, XF, NF)
NACA1418 (JF, XF, NF)
NACA1420 (JF, XF, NF)
NACA1421 (JF, XF, NF)
NACA1424 (JF, XF, NF)
NACA2.4511 (JF, WT, XF, NF)
NACA2206 (JF, XF, NF)
NACA2209 (JF, XF, NF)
NACA2210 (JF, XF, NF)
NACA2212 (JF, XF, NF)
NACA2213 (JF, XF, NF)
NACA2215 (JF, XF, NF)
NACA2216 (JF, XF, NF)
NACA2218 (JF, XF, NF)
NACA2219 (JF, XF, NF)
NACA2221 (JF, XF, NF)
NACA2224 (JF, XF, NF)
NACA2309 (JF, XF, NF)
NACA2310 (JF, XF, NF)
NACA2312 (JF, XF, NF)
NACA2315 (JF, XF, NF)
NACA2317 (JF, XF, NF)
NACA2318 (JF, XF, NF)
NACA2321 (JF, XF, NF)
NACA2324 (JF, XF, NF)
NACA2408 (JF, XF, NF)
NACA2409 (JF, XF, NF)
NACA2410 (JF, XF, NF)
NACA2411 (JF, XF, NF)
NACA2412 (JF, WT, XF, NF)
NACA2414 (JF, WT, XF, NF)
NACA2415 (JF, WT, XF, NF)
NACA2416 (JF, XF, NF)
NACA2417 (JF, XF, NF)
NACA2418 (JF, WT, XF, NF)
NACA2421 (JF, WT, XF, NF)
NACA2424 (JF, WT, XF, NF)
NACA3409 (JF, XF, NF)
NACA3410 (JF, XF, NF)
NACA3412 (JF, XF, NF)
NACA3413 (JF, XF, NF)
NACA3414 (JF, XF, NF)
NACA3415 (JF, XF, NF)
NACA3418 (JF, XF, NF)
NACA3421 (JF, XF, NF)
NACA4312 (JF, XF, NF)
NACA4315 (JF, XF, NF)
NACA4318 (JF, XF, NF)
NACA4321 (JF, XF, NF)
NACA4324 (JF, XF, NF)
NACA4409 (JF, XF, NF)
NACA4410 (JF, XF, NF)
NACA4412 (JF, WT, XF, NF)
NACA4413 (JF, XF, NF)
NACA4415 (JF, WT, XF, NF)
NACA4416 (JF, XF, NF)
NACA4418 (JF, WT, XF, NF)
NACA4421 (JF, WT, XF, NF)
NACA4424 (JF, WT, XF, NF)
NACA5509 (JF, XF, NF)
NACA5510 (JF, XF, NF)
NACA5512 (JF, XF, NF)
NACA5514 (JF, XF, NF)
NACA5515 (JF, XF, NF)
NACA5518 (JF, XF, NF)
NACA5521 (JF, XF, NF)
NACA5524 (JF, XF, NF)
NACA6209 (JF, XF, NF)
NACA6210 (JF, XF, NF)
NACA6212 (JF, XF, NF)
NACA6215 (JF, XF, NF)
NACA6218 (JF, XF, NF)
NACA6221 (JF, XF, NF)
NACA6224 (JF, XF, NF)
NACA6409 (JF, WT, XF, NF)
NACA6410 (JF, XF, NF)
NACA6412 (JF, XF, NF)
NACA6415 (JF, XF, NF)
NACA6418 (JF, XF, NF)
NACA6421 (JF, XF, NF)
NACA6424 (JF, XF, NF)




EPPLER 864 STRUT


EPPLER 864 STRUT AIRFOIL
New! Bulk download of polars in Excel format: e864.xlsx


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 EPPLER 864 STRUT, smooth airfoils, Mach 0:


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

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


Lift: Cl = f(α) = -4.245e-05*α3 + -4.934e-05*α2 + 1.315e-01*α + 1.200e-03
Drag: Cd = f(α) = 7.227e-07*α3 + 1.597e-04*α2 + 6.804e-05*α + 2.989e-02
Moment: Cm = f(α) = 8.439e-07*α3 + 3.326e-07*α2 + -2.472e-03*α + 5.330e-05
−20−1001020−2−1012
Re 500k, JavaFoil DataRe 500k, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section lift coefficient vs angle of attackCl = f(α) = -4.245e-05*α​3​ + -4.934e-05*α​2​ + 1.315e-01*α + 1.200e-03Angle of Attack (deg)Section Lift Coefficient c​l​

−20−10010200.040.060.080.1
Re 500k, JavaFoil DataRe 500k, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section drag coefficient vs angle of attackCd = f(α) = 7.227e-07*α​3​ + 1.597e-04*α​2​ + 6.804e-05*α + 2.989e-02Angle of Attack (deg)Section Drag Coefficient c​d​

−20−1001020−0.04−0.0200.020.04
Re 500k, JavaFoil DataRe 500k, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section moment coefficient vs angle of attackCm = f(α) = 8.439e-07*α​3​ + 3.326e-07*α​2​ + -2.472e-03*α + 5.330e-05Angle of Attack (deg)Section Moment Coefficient c​m​

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


Lift: Cl = f(α) = -4.972e-05*α3 + -6.128e-05*α2 + 1.346e-01*α + 1.054e-03
Drag: Cd = f(α) = 5.467e-07*α3 + 1.458e-04*α2 + 1.079e-04*α + 2.549e-02
Moment: Cm = f(α) = 1.013e-06*α3 + 8.309e-07*α2 + -2.551e-03*α + 1.334e-04
−20−1001020−2−1012
Re 1M, JavaFoil DataRe 1M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section lift coefficient vs angle of attackCl = f(α) = -4.972e-05*α​3​ + -6.128e-05*α​2​ + 1.346e-01*α + 1.054e-03Angle of Attack (deg)Section Lift Coefficient c​l​

−20−10010200.030.040.050.060.070.080.09
Re 1M, JavaFoil DataRe 1M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section drag coefficient vs angle of attackCd = f(α) = 5.467e-07*α​3​ + 1.458e-04*α​2​ + 1.079e-04*α + 2.549e-02Angle of Attack (deg)Section Drag Coefficient c​d​

−20−1001020−0.04−0.0200.020.04
Re 1M, JavaFoil DataRe 1M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section moment coefficient vs angle of attackCm = f(α) = 1.013e-06*α​3​ + 8.309e-07*α​2​ + -2.551e-03*α + 1.334e-04Angle of Attack (deg)Section Moment Coefficient c​m​

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


Lift: Cl = f(α) = -5.215e-05*α3 + -5.230e-05*α2 + 1.361e-01*α + -1.568e-03
Drag: Cd = f(α) = -4.345e-07*α3 + 1.285e-04*α2 + 2.932e-04*α + 2.335e-02
Moment: Cm = f(α) = 1.017e-06*α3 + 4.087e-07*α2 + -2.575e-03*α + 1.170e-04
−20−1001020−2−1012
Re 3M, JavaFoil DataRe 3M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section lift coefficient vs angle of attackCl = f(α) = -5.215e-05*α​3​ + -5.230e-05*α​2​ + 1.361e-01*α + -1.568e-03Angle of Attack (deg)Section Lift Coefficient c​l​

−20−10010200.020.030.040.050.060.070.08
Re 3M, JavaFoil DataRe 3M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section drag coefficient vs angle of attackCd = f(α) = -4.345e-07*α​3​ + 1.285e-04*α​2​ + 2.932e-04*α + 2.335e-02Angle of Attack (deg)Section Drag Coefficient c​d​

−20−1001020−0.04−0.0200.020.04
Re 3M, JavaFoil DataRe 3M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section moment coefficient vs angle of attackCm = f(α) = 1.017e-06*α​3​ + 4.087e-07*α​2​ + -2.575e-03*α + 1.170e-04Angle of Attack (deg)Section Moment Coefficient c​m​

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


Lift: Cl = f(α) = -5.153e-05*α3 + -4.058e-05*α2 + 1.363e-01*α + -3.417e-03
Drag: Cd = f(α) = -5.067e-07*α3 + 1.225e-04*α2 + 2.726e-04*α + 2.297e-02
Moment: Cm = f(α) = 9.943e-07*α3 + -4.890e-08*α2 + -2.580e-03*α + 1.301e-04
−20−1001020−2−1012
Re 6M, JavaFoil DataRe 6M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section lift coefficient vs angle of attackCl = f(α) = -5.153e-05*α​3​ + -4.058e-05*α​2​ + 1.363e-01*α + -3.417e-03Angle of Attack (deg)Section Lift Coefficient c​l​

−20−10010200.020.030.040.050.060.070.08
Re 6M, JavaFoil DataRe 6M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section drag coefficient vs angle of attackCd = f(α) = -5.067e-07*α​3​ + 1.225e-04*α​2​ + 2.726e-04*α + 2.297e-02Angle of Attack (deg)Section Drag Coefficient c​d​

−20−1001020−0.04−0.0200.020.04
Re 6M, JavaFoil DataRe 6M, JavaFoil Curve FitEPPLER 864 STRUTCubic curve fit of JavaFoil data for smooth airfoil at Mach 0Section moment coefficient vs angle of attackCm = f(α) = 9.943e-07*α​3​ + -4.890e-08*α​2​ + -2.580e-03*α + 1.301e-04Angle of Attack (deg)Section Moment Coefficient c​m​