Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing PDF Download

Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing PDF full book. Access full book title Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing by Lawrence Elwood Putnam. Download full books in PDF and EPUB format.

Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing

Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing PDF Author: Lawrence Elwood Putnam
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 76

Book Description
An exploratory investigation has been made at Mach numbers from 0.40 to 0.95 to determine the effects on lift, drag, and pitching moment of blowing a jet exhaust over the upper surface of a 50 deg swept leading-edge wing. Also investigated were the effects of varying the longitudinal and vertical location of the nozzle exit on the induced effects of jet blowing.

Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing

Exploratory Investigation at Mach Numbers from 0.40 to 0.95 of the Effects of Jets Blown Over a Wing PDF Author: Lawrence Elwood Putnam
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 76

Book Description
An exploratory investigation has been made at Mach numbers from 0.40 to 0.95 to determine the effects on lift, drag, and pitching moment of blowing a jet exhaust over the upper surface of a 50 deg swept leading-edge wing. Also investigated were the effects of varying the longitudinal and vertical location of the nozzle exit on the induced effects of jet blowing.

Free-flight Investigation at Mach Numbers Between 0.5 and 1.7 of the Zero-lift Rolling Effectiveness and Drag of Various Surface, Spoiler, and Jet Controls on an 80° Delta-wing Missile

Free-flight Investigation at Mach Numbers Between 0.5 and 1.7 of the Zero-lift Rolling Effectiveness and Drag of Various Surface, Spoiler, and Jet Controls on an 80° Delta-wing Missile PDF Author: Eugene D. Schult
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 52

Book Description

An Analytical Study of the Effects of Jets Located More Than One Jet Diameter Above a Wing at Subsonic Speeds

An Analytical Study of the Effects of Jets Located More Than One Jet Diameter Above a Wing at Subsonic Speeds PDF Author: Lawrence Elwood Putnam
Publisher:
ISBN:
Category : Aircraft exhaust emissions
Languages : en
Pages : 52

Book Description

Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1570

Book Description

Exploratory Investigation of Lift Induced on a Swept-wing by a Two-dimensional Partial Span Deflected Jet at Mach Numbers from 0.20 to 1.30

Exploratory Investigation of Lift Induced on a Swept-wing by a Two-dimensional Partial Span Deflected Jet at Mach Numbers from 0.20 to 1.30 PDF Author: Francis J. Capone
Publisher:
ISBN:
Category :
Languages : en
Pages : 78

Book Description

Exploratory Investigation at Mach Number 4.06 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form - Effects of Various Tail Arrangements on Wing-on and Wing-off Static Longitudinal and Lateral Stability Characteristics

Exploratory Investigation at Mach Number 4.06 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form - Effects of Various Tail Arrangements on Wing-on and Wing-off Static Longitudinal and Lateral Stability Characteristics PDF Author: Robert W. Dunning
Publisher:
ISBN:
Category :
Languages : en
Pages : 60

Book Description

Effects of a Lower Surface Jet on the Lift-drag Ratio of a 45° Sweptback Wing at a Mach Number of 2.01

Effects of a Lower Surface Jet on the Lift-drag Ratio of a 45° Sweptback Wing at a Mach Number of 2.01 PDF Author: Emma Jean Landrum
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 44

Book Description

Exploratory Investigation of the Effect of a Forward-facing Jet on the Bow Shock of a Blunt Body in a Mach Number 6 Free Stream

Exploratory Investigation of the Effect of a Forward-facing Jet on the Bow Shock of a Blunt Body in a Mach Number 6 Free Stream PDF Author: David J. Romeo
Publisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 56

Book Description

Effects of Jet Billowing on Stability of Missile-type Bodies at Mach 3.85

Effects of Jet Billowing on Stability of Missile-type Bodies at Mach 3.85 PDF Author: Reino J. Salmi
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 22

Book Description

Effect of Mach Number on Position Error as Applied to a Pitot-static Tube Located 0.55 Chord Ahead of an Airplane Wing

Effect of Mach Number on Position Error as Applied to a Pitot-static Tube Located 0.55 Chord Ahead of an Airplane Wing PDF Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20

Book Description
Summary: The effect on static-pressure measurements of locating a pitot-static tube 0.55 chord ahead of an airfoil section has been investigated. The tests were conducted in the NACA 24-inch high-speed tunnel on airfoil sections of various thickness ratios over a large range of Mach number. The results show that for a wing having a thickness ratio of 0.15 the measured Mach number, determined from a pitot-static-tube reading, is approximately 0.01 too low at a stream Mach number of 0.4 and approximately 0.03 too low at a Mach number of 0.8.
➤