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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)




SD2083 (9.0%)


New! Bulk download of polars in Excel format: sd2083.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.

−20−10010−0.500.51
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9Re 63.30k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section lift coefficient vs angle of attackAngle of Attack (deg)Section Lift Coefficient c​l
−20−1001000.511.5
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9Re 63.30k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section drag coefficient vs angle of attackAngle of Attack (deg)Section Drag Coefficient c​d
−20−10010−0.08−0.06−0.04−0.0200.020.04
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section moment coefficient vs angle of attackAngle of Attack (deg)Section Moment Coefficient c​m
−20−10010−10010203040
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9Re 63.30k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section lift/drag ratio vs angle of attackAngle of Attack (deg)Section Lift/Drag Coefficient c​l/c​d
−0.500.5100.511.5
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9Re 63.30k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section drag coefficient vs section lift coefficientSection Lift Coefficient c​lSection Drag Coefficient c​d
−0.500.51−10010203040
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9Re 63.30k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section lift/drag ratio vs section lift coefficientSection Lift Coefficient c​lSection Lift/Drag Coefficient c​l/c​d
00.511.5−0.500.51
Re 50k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 50k, Mach 0.00, XFOIL ncrit=9Re 50k, Mach 0.10, XFOIL ncrit=9Re 50k, Mach 0.25, XFOIL ncrit=9Re 63.30k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 63.30k, Mach <=0.25Section lift coefficient vs section drag coefficientSection Drag Coefficient c​dSection Lift Coefficient c​l

−20−10010−0.500.51
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9Re 101.20k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section lift coefficient vs angle of attackAngle of Attack (deg)Section Lift Coefficient c​l
−20−1001000.10.20.30.40.50.6
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9Re 101.20k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section drag coefficient vs angle of attackAngle of Attack (deg)Section Drag Coefficient c​d
−20−10010−0.08−0.06−0.04−0.0200.020.04
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section moment coefficient vs angle of attackAngle of Attack (deg)Section Moment Coefficient c​m
−20−100100204060
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9Re 101.20k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section lift/drag ratio vs angle of attackAngle of Attack (deg)Section Lift/Drag Coefficient c​l/c​d
−0.500.5100.10.20.30.40.50.6
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9Re 101.20k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section drag coefficient vs section lift coefficientSection Lift Coefficient c​lSection Drag Coefficient c​d
−0.500.510204060
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9Re 101.20k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section lift/drag ratio vs section lift coefficientSection Lift Coefficient c​lSection Lift/Drag Coefficient c​l/c​d
00.20.40.6−0.500.51
Re 100k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 100k, Mach 0.00, XFOIL ncrit=9Re 100k, Mach 0.10, XFOIL ncrit=9Re 100k, Mach 0.25, XFOIL ncrit=9Re 101.20k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 101.20k, Mach <=0.25Section lift coefficient vs section drag coefficientSection Drag Coefficient c​dSection Lift Coefficient c​l

−20−10010−0.500.51
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 200.90k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section lift coefficient vs angle of attackAngle of Attack (deg)Section Lift Coefficient c​l
−20−1001000.050.10.150.20.25
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 200.90k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section drag coefficient vs angle of attackAngle of Attack (deg)Section Drag Coefficient c​d
−20−10010−0.08−0.06−0.04−0.0200.020.04
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section moment coefficient vs angle of attackAngle of Attack (deg)Section Moment Coefficient c​m
−20−10010020406080100
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 200.90k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section lift/drag ratio vs angle of attackAngle of Attack (deg)Section Lift/Drag Coefficient c​l/c​d
−0.500.5100.050.10.150.20.25
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 200.90k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section drag coefficient vs section lift coefficientSection Lift Coefficient c​lSection Drag Coefficient c​d
−0.500.51020406080100
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 200.90k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section lift/drag ratio vs section lift coefficientSection Lift Coefficient c​lSection Lift/Drag Coefficient c​l/c​d
00.10.2−0.500.51
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 200.90k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 200.90k, Mach <=0.25Section lift coefficient vs section drag coefficientSection Drag Coefficient c​dSection Lift Coefficient c​l

−20−10010−0.500.51
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 300.70k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section lift coefficient vs angle of attackAngle of Attack (deg)Section Lift Coefficient c​l
−20−1001000.050.10.150.20.25
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 300.70k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section drag coefficient vs angle of attackAngle of Attack (deg)Section Drag Coefficient c​d
−20−10010−0.08−0.06−0.04−0.0200.020.04
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section moment coefficient vs angle of attackAngle of Attack (deg)Section Moment Coefficient c​m
−20−10010020406080100
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 300.70k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section lift/drag ratio vs angle of attackAngle of Attack (deg)Section Lift/Drag Coefficient c​l/c​d
−0.500.5100.050.10.150.20.25
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 300.70k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section drag coefficient vs section lift coefficientSection Lift Coefficient c​lSection Drag Coefficient c​d
−0.500.51020406080100
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 300.70k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section lift/drag ratio vs section lift coefficientSection Lift Coefficient c​lSection Lift/Drag Coefficient c​l/c​d
00.10.2−0.500.51
Re 250k, Mach 0.00, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.10, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.25, JavaFoil+Calcfoil stall+Eppler ext transitionRe 250k, Mach 0.00, XFOIL ncrit=9Re 250k, Mach 0.10, XFOIL ncrit=9Re 250k, Mach 0.25, XFOIL ncrit=9Re 300.70k, Mach 0.00, Wind Tunnel (SoarTech 8)SD2083 (9.0%)Data for smooth airfoil at Re 300.70k, Mach <=0.25Section lift coefficient vs section drag coefficientSection Drag Coefficient c​dSection Lift Coefficient c​l