Investigation Of The Aerodynamic Characteristics In Pitch And Sideslip Of A 45c Swept Wing Airplane Configuration With Various Vertical Locations Of The Wing And Horizontal Tail PDF Download

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Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail

Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail
Author: M. Leroy Spearman
Publisher:
Total Pages: 34
Release: 1957
Genre: Airplanes
ISBN:
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Download Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail Book in PDF, ePub and Kindle

An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.

Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4

Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4
Author: Paul G. Fournier
Publisher:
Total Pages: 34
Release: 1953
Genre: Airplanes
ISBN:
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Download Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4 Book in PDF, ePub and Kindle

The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.

Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section

Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section
Author: Boyd C. Myers
Publisher:
Total Pages: 36
Release: 1949
Genre: Airplane
ISBN:
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Download Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section Book in PDF, ePub and Kindle

This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.

Free-flight Investigation Over a Mach Number Range from 0.74 to 1.43 at Lift Coefficients from Minus 0.15 to 0.75 of an Airplane-configuration Model Having a 52.5 Degree Delta Wing and a Low Swept Horizontal Tail

Free-flight Investigation Over a Mach Number Range from 0.74 to 1.43 at Lift Coefficients from Minus 0.15 to 0.75 of an Airplane-configuration Model Having a 52.5 Degree Delta Wing and a Low Swept Horizontal Tail
Author: Alan B. Kehlet
Publisher:
Total Pages: 41
Release: 1956
Genre: Aerodynamics
ISBN:
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Download Free-flight Investigation Over a Mach Number Range from 0.74 to 1.43 at Lift Coefficients from Minus 0.15 to 0.75 of an Airplane-configuration Model Having a 52.5 Degree Delta Wing and a Low Swept Horizontal Tail Book in PDF, ePub and Kindle

A free-flight investigation over a Mach number range of 0.74 to 1.43 at lift coefficients from -0.15 to 0.75 has been conducted to determine the aerodynamic characteristics of an airplane-configuration model having a 52.5 degree delta wing and a low, swept horizontal tail. The variations in lift-curve slopes and pitching-moment curves were nonlinear with lift coefficient over the lift range covered and increased with increasing lift coefficient. Near the same Mach number and lift coefficient that a similar configuration with a high-position horizontal tail pitched up, the model exhibited stable longitudinal stability characteristics. Good agreement of the present results was obtained with other experimental data and theory.

Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section

Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section
Author: William C. Sleeman
Publisher:
Total Pages: 34
Release: 1949
Genre: Aerofoils
ISBN:
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Download Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees, Aspect Ratio 4, and NACA 65A006 Airfoil Section Book in PDF, ePub and Kindle

This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.