Home eBooks Download › effect of leading and trailing edge flaps on clipped delta wings with and without wing camber at supersonic speeds

Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds

DOWNLOAD
AUDIOBOOK
READ ONLINE

Download Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page

Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds

DOWNLOAD
AUDIOBOOK
READ ONLINE
Author : Gloria Hernandez
language : en
Publisher:
Release Date : 1994

Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds written by Gloria Hernandez and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1994 with Leading edge flaps categories.

Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds

DOWNLOAD
AUDIOBOOK
READ ONLINE
Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-17

Effect Of Leading And Trailing Edge Flaps On Clipped Delta Wings With And Without Wing Camber At Supersonic Speeds written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-17 with categories.

An experimental investigation of the aerodynamic characteristics of thin, moderately swept fighter wings has been conducted to evaluate the effect of camber and twist on the effectiveness of leading- and trailing-edge flaps at supersonic speeds in the Langley Unitary Plan Wind Tunnel. The study geometry consisted of a generic fuselage with camber typical of advanced fighter designs without inlets, canopy, or vertical tail. The model was tested with two wing configurations an uncambered (flat) wing and a cambered and twisted wing. Each wing had an identical clipped delta planform with an inboard leading edge swept back 65 deg and an outboard leading edge swept back 50 deg. The trailing edge was swept forward 25 deg. The leading-edge flaps were deflected 4 deg to 15 deg, and the trailing-edge flaps were deflected from -30 deg to 10 deg. Longitudinal force and moment data were obtained at Mach numbers of 1.60, 1.80, 2.00, and 2.16 for an angle-of-attack range 4 deg to 20 deg at a Reynolds number of 2.16 x 10(exp 6) per foot and for an angle-of-attack range 4 deg to 20 deg at a Reynolds number of 2.0 x 10(exp 6) per foot. Vapor screen, tuft, and oil flow visualization data are also included. Hernandez, Gloria and Wood, Richard M. and Covell, Peter F. Langley Research Center RESEARCH; INVESTIGATION; DESIGN; EXPLORATION...