Download or read book 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 Sweepback at Mach Numbers to 0 92 written by Fred A. Demele and published by . This book was released on 1958 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book 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 written by Fred A. Demele and published by . This book was released on 1958 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 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 written by Fred A. Demele and published by . This book was released on 1959 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 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 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book 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 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 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 written by Earl D. Knechtel and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book 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 written by Kenneth P. Spreemann and published by . This book was released on 1953 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Sweep and Taper on the Longitudinal Characteristics of an Aspect Ratio 3 Wing body Combination at Mach Numbers from 0 6 to 1 4 written by Earl D. Knechtel and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to assess the effects of sweep and taper ratio on the longitudinal characteristics of a wing-body combination at Mach numbers from 0.6 to 14 and for a Reynolds number of 1,500,000. The wings were 3 percent thick and of aspect ratio 3. Leading-edge sweep was varied from 19.1 to 53.1 degrees at a constant taper ratio of 0.4, and taper ratio was varied from 0 to 0.5 at a constant sweep angle of 53.1 degrees.

Download or read book Effects 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 written by Lawrence D. Guy and published by . This book was released on 1954 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3 Having a Full span Flap type Control written by Vernard E. Lockwood and published by . This book was released on 1951 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Effects of Taper Ratio on the Longitudinal Characteristics at Mach Numbers from 0 6 to 1 4 of a Wing body tail Combination Having and Unswept Wing of Aspect Ratio 3 written by James L. Summers and published by . This book was released on 1955 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at Mach numbers from 0.6 to 1.4 and a Reynolds number of 1.5 million are presented. The wings were of aspect ratio 3 with an unswept midchord line and an NACA 64A003 profile. The wing-body combination were tested both with and without a tail.

Download or read book 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 written by Kenneth P. Spreemann and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Full span Trailing edge Elevons on the Transonic Longitudinal Aerodynamic Characteristics of a Wing body Combination Having a 3 percent thick Triangular Wing with 60 Degree Leading edge Sweep written by Chris C. Critzos and published by . This book was released on 1957 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation to determine the effects of full-span trailing-edge flaps on the static longitudinal characteristics of a triangular wing-body combination was conducted in the Langley 16-foot transonic tunnel. This wing had a leading-edge sweep of 60 degrees, an aspect ratio of 2.06, and NACA 65A003 airfoil sections. Force data were obtained for the basic configuration and for the wing with control surfaces deflected for longitudinal control through a deflection range of -15 to 7.5 degrees. Data were obtained at angles of attack generally from 0 degrees to as high as 26 degrees for Mach numbers ranging from 0.80 to 1.05. The Reynolds number varied from 9,800,000 to 10,500,000.

Download or read book Effects of a Leading edge Slat and a Trailing edge Split Flap on the Aerodynamic Characteristics of a Wing fuselage Combination Having a Nearly Triangular Wing of Aspect Ratio 2 9 at Mach Numbers from 0 60 to 0 92 written by Fred A. Demele and published by . This book was released on 1958 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Aerodynamic Characteristics of a Wing Body Combination Having a 52 5 Deg Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of the Square Root of 2 written by William B. Igoe and published by . This book was released on 1961 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees 35 Degrees 45 Degrees and 60 Degrees NACA 65A006 Airfoil Section Aspect Ratio 4 and Taper Ratio 0 6 in Combination with a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1 2 written by Arvo A. Luoma and published by . This book was released on 1951 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Sweep and Taper Ratio on the Longitudinal Characteristics of an Aspect Ratio 3 Wing body Combination at Mach Numbers from 0 6 to 1 4 written by Earl D. Knechtel and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: