If you followed along with this post and tried to build the Reynolds number calculator yourself, way to go! Reynolds number calculator both with automatic Standard Atmosphere integration and a fully manual mode. The length of the airfoil from leading to trailing edge is known as the airfoil chord. The Reynolds number of the flow at the tip station is approximately 100 * 1.0 * 70000 = 7 Millions, at the root the Reynolds number is 17.5 Millions. A 1/4 scale model would fly at roughly 40 m/s and thus would have a tip Reynolds number of 40 * 1.0/4 * 70000 = 0.7 Millions, which is only 1/10 of the full scale plane. A wing planform plotting tool. Use the sliders below to select or deselect geometric variables. velocity is meters/second, chord is meters, kinematic viscosity of air is around $1.48 × 10^-5$. The formulas used are give in CFD-Wiki here.The Schlichting skin-friction formula, as desribed here (equation 21.16 footnote in Schlichting), is used to estimate the local skin-friction for a turbulent boundary layer on a smooth flat plate. The Reynolds number for a pipe or duct expressed in Imperial units. Some additional tools for creation and modification of airfoils have been added to fill the toolbox. Then go to Airfoil Tools.As you make your selections, you can see, in the polar diagrams, the effect Reynolds number has on the lift and drag properties of your wing. Airfoil Nomenclature – NACA 2412. Continue reading "NACA 5 Series Airfoil Generator" The airfoil upper and lower surfaces meet at the leading and trailing edges. You should have something that looks similar to this: NACA 5 Series Tool. The correlation is valid for Re 10^9.The density and viscosity given by default in the form is for air at sea-level and room temperature (20°C). Convert between CAS, EAS, TAS, Mach based on the US Standard Atmosphere. The most common NACA 5-series airfoils are available from the drop-down menu; or alternatively you can design your own. The calculator below can be used to display and extract coordinates of any NACA 5-series airfoil. If supplied with the right food, the computer code will examine your airfoil. To study the relationship between the Reynolds number effect and the entropy generation, we simulated the flow over NACA0012 airfoil under different Reynolds number with turbulence model. For example, a wing with a 10″ chord that is traveling through the air at 67 mph, and at 68-degrees F has a Reynolds numbers of around 500,000. Re = 7745.8 u d h / ν (2a) where. Reynolds Number Calculator. But it’s worth noting that the airfoil tools calculator has values that can be used to simulate different car speeds. If Reynolds Number is >4000, flow is turbulent; If Reynolds Number is <2100, flow is laminar; Otherwise the flow is transitional; The Finished Reynolds Number Calculator. Usually this means Mach numbers between zero and 0.5. The forward section of the airfoil is named the leading edge and the rear the trailing edge. ... NACA 5 Series airfoil plotting tool with text file output. The chord can be varied and either a blunt or sharp leading selected. Contours of entropy generation rate around the NACA0012 airfoil for angle-of-attack ,, and at different Reynolds number can be seen in Figure 6. The Wing Plot Tool allows you to sketch a wing planform by defining a valid combination of the critical wing geometric properties: Wing Area, Wing Span, Aspect Ratio, Taper Ratio, Root Chord, Tip Chord, and Sweep angle (quarter chord). Conversions. The Reynolds number isn’t easy to explain, so I won’t. Reynolds Number is calculated as: velocity × chord/kinematic viscosity of air. You cannot analyze airfoils in transonic or fully supersonic flow with the methods in JavaFoil. Re = Reynolds Number (non dimensional) u = velocity (ft/s) d h = hydraulic diameter (in) ν = kinematic viscosity (cSt) (1 cSt = 10-6 m 2 /s ) The Reynolds Number can be used to determine if flow is laminar, transient or turbulent. Wing Plot Tool.