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
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download 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 full book. Access full book title 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.
| Author | : M. Leroy Spearman |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
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.
| Author | : Paul G. Fournier |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1953 |
| Genre | : Airplanes |
| ISBN | : |
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.
| Author | : Charles F. Whitcomb |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1956 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
Download Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches Book in PDF, ePub and Kindle
An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
| Author | : John W. Draper |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1954 |
| Genre | : Aerodynamics |
| ISBN | : |
Download Investigation of the Aerodynamic Characteristics of a Model Wing-propeller Combination and of the Wing and Propeller Separately at Angles of Attack Up to 90° Book in PDF, ePub and Kindle
This report presents the results of an investigation conducted in the Langley 300 mph 7- 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
| Author | : Donald R. Riley |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1953 |
| Genre | : Aerodynamics |
| ISBN | : |
Download Effect of Horizontal-tail Span and Vertical Location on the Aerodynamic Characteristics of an Unswept Tail Assembly in Sideslip Book in PDF, ePub and Kindle
An investigation has been conducted in the Langley stability tunnel on a vertical-tail model with a stub fuselage in combination with various horizontal tails to determine the effect of horizontal-tail span and vertical location of the horizontal tail relative to the vertical tail on the aerodynamic characteristics of an unswept tail assembly in sideslip.
| Author | : Byron M. Jaquet |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1953 |
| Genre | : Airplanes |
| ISBN | : |
Download Some Low-speed Wind-tunnel Experiments Pertaining to the Longitudinal Stability Characteristics of a 35© Swept-wing Model and an Unswept-wing Model Book in PDF, ePub and Kindle
| Author | : Rodger L. Naeseth |
| Publisher | : |
| Total Pages | : 88 |
| Release | : 1963 |
| Genre | : Aerodynamics |
| ISBN | : |
Download Low-speed Investigation of the Effects of Wing Sweep on the Aerodynamic Characteristics of Parawings Having Equal-length Leading Edges and Keel Book in PDF, ePub and Kindle
An investigation has been made in the Langley 300-MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a related series of parawings in which wing sweep was the primary variable. The leading-edge sweep angles varied from 400 to 750 and the three basic parawings had flat-planform sweep angles of 350, 450, and 550. The canopies of the wings were made of fabric. Tests were made at an airspeed of 38.6 mph and a Reynolds number of approximately 1.5 X 106. The maximum angle-of-attack range was from 140 to 530 for the wings having a canopy of 350 flat-planform sweep. A limited investigation of lateral characteristics was made for sideslip angles from approximately -50 to 160 for two angles of attack, and lateral stability derivatives were obtained for some configurations through a angle-of-attack range. Forces and moments acting on the wing and apex hinge moments were measured.
| Author | : William P. Henderson |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1964 |
| Genre | : Airplanes |
| ISBN | : |
Download Effect of Wing Pivot Location on Longitudinal Aerodynamic Characteristics of a Variable-sweep Wing Having an M Planform Book in PDF, ePub and Kindle
| Author | : Howard F. Savage |
| Publisher | : |
| Total Pages | : 662 |
| Release | : 1957 |
| Genre | : Aerodynamics |
| ISBN | : |
Download The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 Book in PDF, ePub and Kindle
An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
| Author | : Edward C. Polhamus |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1958 |
| Genre | : Airplanes |
| ISBN | : |
Download Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing Book in PDF, ePub and Kindle
A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
