1987-10-01

Full-Scale Semi-Span Tests of an Advanced NLF Business Jet Wing 871860

An investigation has been conducted in the NASA Langley Research Center's 30- by 60-Foot Wind Tunnel on a full-scale semi-span model to evaluate and document the low-speed, high-lift characteristics of a business-jet class wing utilizing the HSNLF(1)-0213 airfoil section and a single slotted flap system. In addition to the high-lift studies, evaluations of boundary layer transition effects, the effectiveness of a segmented leading-edge droop for improved stall/spin resistance, and roll control effectiveness with and without flap deflection were made.
The wind-tunnel investigation showed that deployment of a single-slotted trailing-edge flap provided substantial increments in lift. Fixed transition studies indicated no adverse effects on lift and pitching-moment characteristics for either the cruise or landing configuration. Sub-scale roll damping tests also indicated that stall/spin resistance could be enhanced through the use of a properly designed leading-edge droop.

SAE MOBILUS

Subscribers can view annotate, and download all of SAE's content. Learn More »

Access SAE MOBILUS »

Members save up to 18% off list price.
Login to see discount.
Special Offer: Download multiple Technical Papers each year? TechSelect is a cost-effective subscription option to select and download 12-100 full-text Technical Papers per year. Find more information here.
We also recommend:
TECHNICAL PAPER

Evaluation of a Complete Wake Integral for the Drag of a Car-Like Shape

840577

View Details

TECHNICAL PAPER

A Nonlinear Transient Formulation of UHB Aeroelastic Response and Stability: Part 1 - Theoretical Formulation

892322

View Details

TECHNICAL PAPER

Experimental Analysis of the Underbody Pressure Distribution of a Series Vehicle on the Road and in the Wind Tunnel

2008-01-0802

View Details

X