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Aerodynamic characteristics of a wing near its tip using panel method. Panel ho ni yoru tandokuyoku yokutan fukin no kuryoku tokusei

Journal Article:

Abstract

The study described in this paper is intended to evaluate the aerodynamic characteristics of a turbo machine wing or an aircraft wing near its tip, using the panel method. The paper describes the case of a rectangular wing with a large aspect ratio. The introduced linear simultaneous equation was solved using a computer, and compared with the experimental result. The result may be summarized as follows: The distribution of pressure on the wing near its tip using the panel method takes the same shape as that for the experimental result; the negative pressure calculated close to the wing's trailing edge near the wing tip is a result of a three-dimensional effect of the flow along the wing width; the calculation and the experiment showed an increase in local lift coefficient and locally induced resistance coefficient in the vicinity of wing tip; the speed component in the y'' direction explains the structure of the wing surface velocity forming wing backwash vortex given by the lift linearity theory; and the result of calculation on the pressure distribution in the wing chord direction near the wing tip is very close to the experimental result except for the wing flank in the close vicinity  More>>
Authors:
Choi, J; [1]  Sugiyama, Y [2] 
  1. Nagoya University, Nagoya (Japan)
  2. Nagoya University, Nagoya (Japan). Faculty of Engineering
Publication Date:
Jan 05, 1992
Product Type:
Journal Article
Reference Number:
NEDO-92-911269; EDB-92-130727
Resource Relation:
Journal Name: Nippon Koku Uchu Gakkai-Shi (Journal of the Japan Society for Aeronautical and Space Sciences); (Japan); Journal Volume: 40:456
Subject:
99 GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE; 42 ENGINEERING; AERODYNAMICS; COMPUTERS; LINEAR ABSORPTION MODELS; PRESSURE DEPENDENCE; VELOCITY; AIRFOILS; AIRCRAFT; ASPECT RATIO; TURBINE BLADES; DRAG; LEVITATION; FLUID MECHANICS; MATHEMATICAL MODELS; MECHANICS; PARTICLE MODELS; 990200* - Mathematics & Computers; 420400 - Engineering- Heat Transfer & Fluid Flow
OSTI ID:
7233572
Country of Origin:
Japan
Language:
Japanese
Other Identifying Numbers:
Journal ID: ISSN 0021-4663; CODEN: NKGAB
Submitting Site:
NEDO
Size:
Pages: 45-53
Announcement Date:

Journal Article:

Citation Formats

Choi, J, and Sugiyama, Y. Aerodynamic characteristics of a wing near its tip using panel method. Panel ho ni yoru tandokuyoku yokutan fukin no kuryoku tokusei. Japan: N. p., 1992. Web.
Choi, J, & Sugiyama, Y. Aerodynamic characteristics of a wing near its tip using panel method. Panel ho ni yoru tandokuyoku yokutan fukin no kuryoku tokusei. Japan.
Choi, J, and Sugiyama, Y. 1992. "Aerodynamic characteristics of a wing near its tip using panel method. Panel ho ni yoru tandokuyoku yokutan fukin no kuryoku tokusei." Japan.
@misc{etde_7233572,
title = {Aerodynamic characteristics of a wing near its tip using panel method. Panel ho ni yoru tandokuyoku yokutan fukin no kuryoku tokusei}
author = {Choi, J, and Sugiyama, Y}
abstractNote = {The study described in this paper is intended to evaluate the aerodynamic characteristics of a turbo machine wing or an aircraft wing near its tip, using the panel method. The paper describes the case of a rectangular wing with a large aspect ratio. The introduced linear simultaneous equation was solved using a computer, and compared with the experimental result. The result may be summarized as follows: The distribution of pressure on the wing near its tip using the panel method takes the same shape as that for the experimental result; the negative pressure calculated close to the wing's trailing edge near the wing tip is a result of a three-dimensional effect of the flow along the wing width; the calculation and the experiment showed an increase in local lift coefficient and locally induced resistance coefficient in the vicinity of wing tip; the speed component in the y'' direction explains the structure of the wing surface velocity forming wing backwash vortex given by the lift linearity theory; and the result of calculation on the pressure distribution in the wing chord direction near the wing tip is very close to the experimental result except for the wing flank in the close vicinity of the wing tip upstream of the wing chord middle point. 11 refs., 13 figs.}
journal = {Nippon Koku Uchu Gakkai-Shi (Journal of the Japan Society for Aeronautical and Space Sciences); (Japan)}
volume = {40:456}
journal type = {AC}
place = {Japan}
year = {1992}
month = {Jan}
}