Coefficient of drag Fuselage Contribution
Coefficient of drag Fuselage Contribution Read More »
Aerodynamics Calculator
Boost your aerodynamic endeavors with the online aerodynamics calculator by ToDo Calculator. Tailored for aerospace engineers, researchers, and enthusiasts, this versatile tool facilitates a myriad of aerodynamics calculations. Leveraging the robust capabilities of ToDo Calculator, it delivers precise solutions across various parameters, from airfoil analysis to lift and moment calculations. With its intuitive interface, this calculator demystifies complex aerodynamic computations, empowering both professionals and students alike. Whether you’re crafting aircraft or delving into fluid dynamics, this resource accelerates your aerodynamics analysis, ensuring optimal performance in aerospace projects.
Calculate Parasite Drag Coefficient for horizontal and vertical tail contribution
The drag polar of an airplane relates the drag coefficient (CDC_DCD​) to the lift coefficient (CLC_LCL​). It is expressed as: CD=CD0+kCL2C_D = C_{D0} + kC_L^2CD​=CD0​+kCL2​ Here, CD0C_{D0}CD0​ is the parasite drag coefficient, and kkk is the coefficient of induced drag. To estimate the drag polar, we need to calculate CD0C_{D0}CD0​ and kkk.
Calculate Parasite Drag Coefficient for horizontal and vertical tail contribution Read More »