Approximate Method of Calculating the Aerodynamic Load Distribution on a Low-Flying Wing with a Fuselage,
Abstract
A technique is proposed for the numerical calculation of the aerodynamic load distribution under uniform motion of a wing with an angle of sweepback and an angle of heel, and with a fuselage in the form of an infinite circular cylinder and a zero angle of attack over a solid screen. The wing is modeled by a system of discrete oblique horseshoe shaped vortices. A scheme with 18 vortices was selected. The calculations showed how the fuselage has a considerable effect on the distribution of aerodynamic load along the wing, the effect being especially great in the motion of the system close to a solid screen. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 26, 1973
- Accession Number
- AD0756075
Entities
People
- L. G. Tsvetkov
Organizations
- National Air and Space Intelligence Center