This chapter reviews aircraft aerodynamics both at the fundamental and applied levels. Similarity parameters and boundary conditions in viscous, thermally conducting compressible flows are fundamental to the study of aircraft aerodynamics. In flows with a high Reynolds number, boundary‐layer formation and its behavior on bodies in motion hold the key to all viscous aerodynamic studies. These include profile and parasite drag. The chapter presents finite wing using classical Prandtl wing theory, followed by the modern view on bell spanloading and its impact on aerodynamic efficiency and proverse yaw phenomenon. Mach number is related to pressure distribution, compressibility effects, wave formations, and wave drag. In 1935, A. Busemann introduced the concept of wing sweep to alleviate drag divergence at supersonic/transonic Mach numbers in what became a historic gathering of aerodynamics pioneers at the 5th Volta Congress held in Rome, Italy.
Aircraft Aerodynamics – A Review
2019-11-18
91 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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