Design of a Basic Airfoil for a Slightly Swept Wing. Part 1: Theoretical Transonic Airfoil Design
Design of a Basic Airfoil for a Slightly Swept Wing. Part 1: Theoretical Transonic Airfoil Design
- New search for: G. Wichmann
- New search for: G. Wichmann
A wing based on the A-300 aircraft with leading edge sweep reduced from 30 to 13.5 deg at the same flight Mach number was designed using transonic wing technology. A method based on the complete potential flow equation was used. Flow around a specified initial profile is first calculated at the design point, the principle of elliptic continuation of the basic equation (fictitious gas concept) being used in the supersonic part of the flow to avoid the appearance of discontinuities. Using the sonic line so determined as the initial condition, the actual supersonic flow and its associated new supersonic contour is determined using a characteristic method. Calculations at the design point and off-design flight conditions show that requirements of free stream Mach number = 0.77, profile lift coefficient = 0.6, relative wing thickness = 0.11, and pitching moment or = -0.13 are met.
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Design of a Basic Airfoil for a Slightly Swept Wing. Part 1: Theoretical Transonic Airfoil Design
1985
50 pages
Report
No indication
English
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