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Ventilation Curve – Plot VE vs. VO 2 or Watts or Time – The point at which there is a non‐linear increase in ventilation; V‐Slope Method – Plot VO 2 vs. VCO 2 – The point at which the increase in VCO 2 is greater than the increase in VO 2
Simulation of an airplane using Open VOGEL, an open source framework for aerodynamic simulations based in the UVLM. The Vortex lattice method, (VLM), is a numerical method used in computational fluid dynamics, mainly in the early stages of aircraft design and in aerodynamic education at university level.
The Kutta–Joukowski theorem is a fundamental theorem in aerodynamics used for the calculation of lift of an airfoil (and any two-dimensional body including circular cylinders) translating in a uniform fluid at a constant speed so large that the flow seen in the body-fixed frame is steady and unseparated.
Dimensionless numbers (or characteristic numbers) have an important role in analyzing the behavior of fluids and their flow as well as in other transport phenomena. [1] They include the Reynolds and the Mach numbers, which describe as ratios the relative magnitude of fluid and physical system characteristics, such as density, viscosity, speed of sound, and flow speed.
In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. [1] With a given upstream Mach number, the post-shock Mach number can be calculated along with the pressure, density, temperature, and stagnation pressure ratios.
Anderson, John D. (2007), Fundamentals of Aerodynamics, Section 3.4 (4th edition), McGraw-Hill, New York USA. ISBN 978-0-07-295046-5 Gracey, William (1980), "Measurement of Aircraft Speed and Altitude" Archived 2021-09-26 at the Wayback Machine (11 MB), NASA Reference Publication 1046.
The advance ratio is the inverse of the tip speed ratio, , used in wind turbine aerodynamics: [6] μ = λ − 1 {\displaystyle \mu =\lambda ^{-1}} . In operation, propellers and rotors are generally spinning, but could be immersed in a stationary fluid.
In February 1976, work commenced to automate the methods contained in the USAF Stability and Control DATCOM, specifically those contained in sections 4, 5, 6 and 7.The work was performed by the McDonnell Douglas Corporation under contract with the United States Air Force in conjunction with engineers at the Air Force Flight Dynamics Laboratory in Wright-Patterson Air Force Base.