A summary of recent large-scale research on high-lift devices

19660015323 · NASA · 1966

Public domain · NASATechnical Reports

Overview

A brief summary of recent 40- by 80-foot wind-tunnel investigations of large-scale models equipped with various high-lift devices is presented. The basic high-lift concepts that were investigated were the externally blown flap, the augmentor wing, and the rotating-cylinder flap. The scope of this…

Publisher: NASA
Document: 19660015323
Year: 1966
Pages: 17

Key points

The document discusses various configurations of high-lift devices, including externally blown flaps and augmentor wings.
Wind-tunnel models are utilized to study the performance of different high-lift device designs.
The leading-edge slat and auxiliary flap configurations are highlighted in the research.
The aspect ratio of wings is noted, with specific values provided for different models.
The document includes visual representations of the wind-tunnel models for better understanding.

Frequently asked questions

What types of high-lift devices are discussed in the document?

The document discusses externally blown flaps, augmentor wings, leading-edge slats, and auxiliary flaps.

How are the high-lift devices tested?

The high-lift devices are tested using wind-tunnel models to evaluate their performance.

What is the significance of wing aspect ratio in the research?

The aspect ratio of wings is significant as it affects the performance of the high-lift devices, with specific values provided for different configurations.

Are there visual aids included in the document?

Yes, the document includes figures that visually represent the wind-tunnel models of the high-lift devices.

What is the purpose of the research summarized in the document?

The purpose of the research is to explore and summarize findings related to the performance of various high-lift device configurations.

Document

EXTERNALLY BLOWN FLAP CON F I GURAT ION LEADING-EDGE SLAT AUXILIAR% FLAP %"X WING ASPECT RATIO.5.4 HALF-SPAN FLAPS Figure 1 WIND-TUNNEL MODEL WITH EXTERNALLY BLOWN FLAPS Figure 2 A-34818.1 AUGMENTOR WING AUGMENTOR UPPER DOOR I I LEADING-EDGE WING ASPECT RATIO = 8 CJ AUGMENTOR SPAN/b = . 6 AUGMENTATION RATIO = 1.4 Figure 3 WIND-TUNNEL MODEL WITH AN AUGMENTOR WING