Method for the prediction of wing maximum lift

Valarezo, Walter O.; Chin, Vincent

doi:10.2514/3.46461

Cited by 43 publications

(33 citation statements)

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“…For this reason Valerezo and Chin [66] combined a panel method [81] and a semi-empirical pressure difference rule (PDR) to obtain remarkably accurate maximum lift predictions for complex 3D configurations. The PDR is a refinement of an empirical method first described by Loftin and von Doenhoff [88].…”

Section: Three-dimensional Methodsmentioning

confidence: 99%

“…Given this lack of consistency, Greenman et al [49][50][51] implemented a socalled pressure difference rule to provide a 'sanity check' on the maximum lift predictions obtained with INS2D. The semi-empirical pressure difference rule, developed by Valerezo and Chin [66], allows for the prediction of maximum lift based on the pressure difference between the suction peak and trailing edge. Once this pressure difference reaches a certain value that is Reynolds number and Mach number dependent, maximum lift is marked.…”

Section: Two-dimensional Methodsmentioning

confidence: 99%

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The aerodynamic design of multi-element high-lift systems for transport airplanes

Dam¹

2002

Progress in Aerospace Sciences

254

109

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High-lift systems have a major influence on the sizing, economics, and safety of most transport airplane configurations. The combination of complexity in flow physics, geometry, and system support and actuation has historically led to a lengthy and experiment intensive development process. However, during the recent past engineering design has changed significantly as a result of rapid developments in computational hardware and software. In aerodynamic design, computational methods are slowly superseding empirical methods and design engineers are spending more and more time applying computational tools instead of conducting physical experiments to design and analyze aircraft including their high-lift systems. The purpose of this paper is to review recent developments in aerodynamic design and analysis methods for multi-element high-lift systems on transport airplanes. Attention is also paid to the associated mechanical and cost problems since a multi-element high-lift system must be as simple and economical as possible while meeting the required aerodynamic performance levels. r

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Section: Three-dimensional Methodsmentioning

confidence: 99%

Section: Two-dimensional Methodsmentioning

confidence: 99%

The aerodynamic design of multi-element high-lift systems for transport airplanes

Dam¹

2002

Progress in Aerospace Sciences

254

109

View full text Add to dashboard Cite

show abstract

“…Using the free stream Mach number the critical pressure difference at each spanwise section is determined from Figure 2.22. Figure 2.22: Critical pressure difference for given chord Reynolds number [46] 3. With the critical pressure differences determined, an "allowable" pressure difference distribution is constructed.…”

Section: Semi-emperical Methodsmentioning

confidence: 99%

“…While semi-empirical methods partially remove the restriction of being able to analyze only conventional designs, care should be taken in using these methods on novel design concepts. PRESSURE DIFFERENCE RULE A promising semi-emperical method of computing the wing C L max has been developed by Valarezo and Chin [46] and is called the Pressure Difference Rule (PDR). They observed that for a given chord Reynolds number and free stream Mach number, there exists a relation between the pressure of the suction peak and trailing edge pressure, and wing stall.…”

Section: Semi-emperical Methodsmentioning

confidence: 99%