Span Load Distribution for Tapered Wings with Partial-Span Flaps.
Abstract
Tables are given for determining the load distribution of tapered wings with partial-span flaps placed either at the center or at the wing tips. Seventy-two wing-flap combinations including two aspect ratios, four taper ratios, and nine flap lengths are included. The distributions for the flapped wing are divided into two parts, one a zero lift distribution due primarily to the flaps and the other an additional lift distribution due to an angle of attack of the wing as a whole. Comparisons between theoretical and experimental results for wings indicate that the theory may be used to predict the load distribution with sufficient accuracy for structural purposes. Simple computing forms are included for determining, by the Lotz method, the theoretical loadings for a combination of any wing with any flap. A discussion of the method is given showing: (1) the effect on the load distribution of increasing the number of harmonics for a wing with partial-span flaps; and (2) the effect of increasing the number of points used across the semispan for a wing of unfair plan form. (KAR) P. 5
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1937
- Accession Number
- ADA298182
Entities
People
- H. A. Pearson
Organizations
- National Aeronautics and Space Administration