A Method for the Determination of the Spanwise Load Distribution of a Flexible Swept Wing at Subsonic Speeds
Abstract
A method is presented for the determination of the spanwise load distribution of a flexible swept wing at subsonic speeds. The method is based on a relaxation approach utilizing aerodynamic loadings obtained from previously published work (NACA Rep. 921, 1948) based on Weissinger's simplified lifting-surface theory together with simple beam theory. The solution is expressed in a convenient form such that the amount of detailed computing involved when extensive aeroelastic calculations for many flight conditions are desired is reduced to that for a single set of flight conditions. The method is simplified further by an abbreviated solution to the relaxation process. Sample computing forms and a numerical example are presented to illustrate the method.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1951
- Accession Number
- ADA381907
Entities
People
- Harvey H. Brown
- Richard B. Skoog
Organizations
- National Aeronautics and Space Administration