Flight Determination of Wing and Tail Loads on a Fighter-Type Airplane by Means of Strain-Gage Measurements
Abstract
A flight investigation was conducted to determine the contributions of wing, tail, and fuselage to the total airplane lift of a propeller-driven fighter-type airplane. The tests covered a Mach number range from 0.2 to 0.8. The loads on the various airplane components were measured by the use of calibrated strain-gage installations located at the roots of the wings and horizontal tail surfaces.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1948
- Accession Number
- ADA380898
Entities
People
- William S. Aiken Jr.
Organizations
- National Aeronautics and Space Administration