Pub Date : 1998-03-01DOI: 10.1016/S1369-8869(98)00004-4
Hamid R. Saeedipour, T. Neil Stevenson
The complexity of the equations and the number of parameters involved make it difficult to appreciate how a change to the specification of an aircraft alters the final design. The analysis in this paper gives students an insight into the interaction between the many important parameters in the design. The equations are linearised and it becomes possible to answer quantitatively questions of the form: “AircraftA has been designed to a given specification. AircraftB is to be designed with geometrically similar wings and horizontal tail and with scaled engines but with a small change to a particular specification, say the range is increased by 5%. What are the differences between aircraftA and aircraftB?”
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Pub Date : 1998-03-01DOI: 10.1016/S1369-8869(98)00008-1
Todd W. Riddle , Stuart E. Rogers , James C. Ross , Russell M. Cummings
A three-dimensional numerical examination of vortex trapping on the upper surface of a swept wing is presented. A baseline wing is utilized with the NACA 0012 airfoil section, no twist, and a taper ratio of one. Trapping is performed on this wing swept to 60°. Vortex trapping is accomplished by the addition of two fences placed parallel to each other and to the leading edge. The incompressible Navier–Stokes flow solver, INS3D, is used to model the flowfield around the wing geometry. The aerodynamic forces and moments obtained from computations are then compared to experimental results for a similar wing. Experimental and computational results show similar trends for lift, drag, and pitching-moment. The results show a high drag penalty for moderate increases in lift and pitching moment over the baseline values. Qualitative analyses of the numerical results show pressure gradients throughout the flowfield to be the drivers of the trapped vortex, as well as of the drag increases and downstream momentum losses. Recommendations are given on ways to decrease the pressure gradient influences and to increase the effectiveness of vortex trapping on swept-wing planforms.
{"title":"A numerical analysis of three-dimensional vortex trapping","authors":"Todd W. Riddle , Stuart E. Rogers , James C. Ross , Russell M. Cummings","doi":"10.1016/S1369-8869(98)00008-1","DOIUrl":"10.1016/S1369-8869(98)00008-1","url":null,"abstract":"<div><p>A three-dimensional numerical examination of vortex trapping on the upper surface of a swept wing is presented. A baseline wing is utilized with the NACA 0012 airfoil section, no twist, and a taper ratio of one. Trapping is performed on this wing swept to 60°. Vortex trapping is accomplished by the addition of two fences placed parallel to each other and to the leading edge. The incompressible Navier–Stokes flow solver, INS3D, is used to model the flowfield around the wing geometry. The aerodynamic forces and moments obtained from computations are then compared to experimental results for a similar wing. Experimental and computational results show similar trends for lift, drag, and pitching-moment. The results show a high drag penalty for moderate increases in lift and pitching moment over the baseline values. Qualitative analyses of the numerical results show pressure gradients throughout the flowfield to be the drivers of the trapped vortex, as well as of the drag increases and downstream momentum losses. Recommendations are given on ways to decrease the pressure gradient influences and to increase the effectiveness of vortex trapping on swept-wing planforms.</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 1","pages":"Pages 61-73"},"PeriodicalIF":0.0,"publicationDate":"1998-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00008-1","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77893502","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1992-06-22DOI: 10.1016/S1369-8869(00)00007-0
S. Murman, Y. Rizk, L. Schiff
{"title":"Coupled numerical simulation of the external and engine inlet flows for the F-18 at large incidence","authors":"S. Murman, Y. Rizk, L. Schiff","doi":"10.1016/S1369-8869(00)00007-0","DOIUrl":"https://doi.org/10.1016/S1369-8869(00)00007-0","url":null,"abstract":"","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"28 1","pages":"65-77"},"PeriodicalIF":0.0,"publicationDate":"1992-06-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83407530","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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