Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps

Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps
Author :
Publisher :
Total Pages : 72
Release :
ISBN-10 : OCLC:1109564967
ISBN-13 :
Rating : 4/5 (67 Downloads)

Book Synopsis Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps by : Roy H. Lange

Download or read book Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps written by Roy H. Lange and published by . This book was released on 1949 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:


Investigation at Large Scale of the Pressure Distribution and Flow Phenomena Over a Wing with the Leading Edge Swept Back 47.5 Degrees Having Circular-arc Airfoil Sections and Equipped with Drooped-nose and Plain Flaps Related Books

Influence of Airfoil Geometry on Delta Wing Leading-edge Vortices and Vortex-induced Aerodynamics at Supersonic Speeds
Language: en
Pages: 88
Authors: Richard M. Wood
Categories: Aerodynamics, Supersonic
Type: BOOK - Published: 1992 - Publisher:

DOWNLOAD EBOOK

Pressure-distribution Measurements Over a 45 Degree Sweptback Wing at Transonic Speeds by the NACA Wing-flow Method
Language: en
Pages: 42
Authors: Edward C. B. Danforth
Categories: Aerodynamic load
Type: BOOK - Published: 1951 - Publisher:

DOWNLOAD EBOOK

Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method.