![The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92 PDF](https://books.google.com/books/content/images/frontcover/6o2LPgAACAAJ?fife=w150-h200)
Author: Fred A. DemelePublisher:
ISBN:
Category :
Languages : en
Pages : 57
Book Description
The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92
![The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92 PDF](https://books.google.com/books/content/images/frontcover/6o2LPgAACAAJ?fife=w80-h100)
Author: Fred A. DemeleThe Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 Degrees of Sweepback at Mach Numbers to 0.92
Author: Fred A. DemelePublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 57
Book Description
An investigation has been made to detemnine the effects of an inverse-taper leading-edge flap on the drag and on the static-longitudinal characteristics of a swept-wing-body conibination. The wing had 45 degrees of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of 3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16 degrees.
The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Loading Characteristics of a 45° Sweptback Wing at Mach Numbers to 0.90
Author: Fred A. DemeleInvestigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4
Author: Kenneth P. SpreemannPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 644
Book Description
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers of 0.40 to 0.93 of a 45© Sweptback Wing of Aspect Ratio 4
Author: Kenneth P. SpreemannPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Book Description
Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4
Author: Earl D. KnechtelPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Investigation of the Effects of Leading-edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers from 0.40 to 0.93 of a Wing-fuselage Configuration with a 45 Degree Sweptback Wing of Aspect Ratio 4
Author: Kenneth P. SpreemannEffects of Overhang Balance on the Hinge-moment and Effectiveness Characteristics of an Unswept Trailing-edge Control on a 60 Degree Delta Wing at Transonic and Supersonic Speeds
Author: Lawrence D. GuyPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
A wind-tunnel investigation has been made of two unswept, partial-span, flap-type controls (differing only in hinge-line location) mounted on a 60 degree delta wing. One control was unbalanced and the other has a 100-percent overhang balance. Control hinge moments as well as aerodynamic characteristics of the complete wing-body combination were obtained for control deflections from 0 to 40 degrees over an angle-of-attack range of plus or minus 12 degrees at Mach numbers from 0.75 to 1.96. Reynolds numbers varied between 2,200,000 and 2,200,000. Expressions derived from linear theory for the hinge-moment coefficient due to angle of attack for unswept partial-span controls (which extend neither to the wing tip nor to the wing center line) on triangular wings having subsonic leading edges are given in an appendix.
Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4
Author: Kenneth P. SpreemannAerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3 Having a Full-span Flap-type Control
Author: Vernard E. LockwoodPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 35
Book Description
The aerodynamic characteristics in pitch and the control characteristics of a wing-flap combination have been determined for a wing having a quarter-chord line sweep of 45.58 degrees, an aspect ratio of 3, a taper ratio of 0.5, and an NACA 64A010 airfoil section measured in a plane at an angle of 45 degrees to the plane of symmetry. The wing employed a 25.4-percent-chord full-span plain flap-type control with a removable seal so that the effects of a relatively small gap could be determined. The investigation covered a Mach number range from 0.6 to 1.17 at angles of attack of 0, 4, and 8 degrees through a control-surface deflection range from -27 degrees to approximately 5 degrees. These data were obtained from the Langley high-speed 7- by 10-foot-tunnel transonic bump.