Relative Loading on Biplane Wings
Abstract
The accuracy of a biplane stress analysis depends greatly on the accuracy with which the loads on each wing can be determined. The division of the load between biplane wings has usually been determined in the current stress analysis methods from a chart giving the relative efficiency as a function of gap/chord ratio and stagger. This relative efficiency or ratio of the lift coefficient of the upper wing to lift coefficient of the lower wing has been based on the average values at high lift coefficients and therefore does not necessarily hold true for all lift coefficients. Recent improvements in stress analysis methods have made it necessary to revise and to extend the loading curves to cover all conditions of flight. This paper is concerned with a study of existing biplane data in connection with such a revision.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1933
- Accession Number
- ADA278018
Entities
People
- Walter S. Diehl
Organizations
- National Aeronautics and Space Administration