Drs estudio comparativo sobre la fuerza de drag y downforce (equivalente de lift)
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This document discusses the aerodynamic analysis of a rear wing on a vehicle with and without the DRS (Drag Reduction System) activated. It provides calculations of lift, drag, pressure distributions, and lift to drag ratios for the rear wing in both configurations. References used in the analysis are also listed at the end.
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This document presents the analysis of non-lifting potential flow past a thin symmetric hydrofoil using a finite difference method. The objectives are to solve the potential flow problem around a 2D hydrofoil and calculate the pressure distribution. A NACA 0012 hydrofoil is used. Governing equations and boundary conditions for the potential flow are described. A structured algebraic grid is used to generate points around the hydrofoil. Finite difference equations are derived and discretized on the grid points. The pressure coefficient is then calculated and compared to experimental results, showing good agreement.
Aeroelasticity_A_R_10241445
This document summarizes a student's analysis of aeroelastic divergence and flutter for a swept wing. In part 1, the student calculates the required stiffness (K) to achieve a specified divergence speed for a given wing configuration. A parametric study shows that increasing flexural rigidity (EI), torsional rigidity (GJ), or stiffness (K) increases divergence speed as expected. With K=0, the student estimates possible forward sweep angles that would achieve the required divergence speed. In part 2, the student considers flutter of the flexible wing and calculates flutter speeds for different configurations.
20 ms-me-amd-06 (simple linear regression)
This document discusses simple linear regression. It defines simple linear regression as having one independent variable and a linear relationship between the independent and dependent variables. The simple linear regression model is presented as Yi = β0 + β1Xi + Ԑi, where β0 is the intercept and β1 is the slope. Formulas to estimate the regression line and calculate statistics like the F-test, t-test, and R-squared are also provided. An example is worked through to demonstrate how to apply simple linear regression to a real data set.
Helicopter rotor dynamics
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Design and Analysis of Loading Bracket for Landing Gear Strength Test
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Drs estudio comparativo sobre la fuerza de drag y downforce (equivalente de lift)
- 1. Universidad San Francisco de Quito Aerodinámica Erik Proaño
- 7. Alerón Trasero (DRS desactivado)
- 8. Superficies
- 9. Streamlines
- 10. Campo Vectorial de Velocidades
- 12. Pressure Coutour
- 13. 퐿푖푓푡 = −6172,68202 [푁 푚] 퐷푟푎푔 = 8358,291163 [푁 푚] 푀푝푒푟푓푖푙 푠푢푝푒푟푖표푟 = 1069,92881 [푁] 푀푝푒푟푓푖 푖푛푓푒푟푖표푟 = 666,98191[푁] Lift to Drag ratio 퐿 퐷 = 0,73851 Cálculos
- 14. Alerón Trasero (DRS activado)
- 15. Superficies
- 16. Streamlines
- 17. Campo Vectorial de Velocidades
- 19. Pressure Coutour
- 20. 퐿푖푓푡 = −3100,25735 [푁 푚] 퐷푟푎푔 = 3686,293587 [푁 푚] 푀푝푒푟푓푖푙 푠푢푝푒푟푖표푟 = 409,81225 [푁] 푀푝푒푟푓푖 푖푛푓푒푟푖표푟 = 311,90727[푁] Lift to Drag ratio 퐿 퐷 = 0,841023 Cálculos
- 21. Referencias Abbott, I., & Von Doenhoff, A. (1959). Theory of Wing Sections. New York: Dover Publications. Anderson, D. (2010).Fundamentals of Aerodynamics. Maryland .McGraw Hill. White, F. (2008). Fluid Mechanics (6th ed.). Rhode Island: McGraw Hill.