Results of study made with 45° swept-wing model; comparison with results for configuration with leading edge slats is included; devices provided only slight improvement of longitudinal stability characteristics but decreased aircraft drag coefficients at moderate and high lifting conditions.
Transonic investigation of aerodynamic characteristics of swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches
NASA -- Tech Note
1961
30 pages
Report
Englisch
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