Download or read book Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Robert F. Thompson and published by . This book was released on 1950 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.

Download or read book Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Raymond D. Vogler and published by . This book was released on 1949 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of an NACA research program, an investigation by the transonic-bump method through a Mach range of 0.6 to 1.2 has been made in the Langley high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of 30-percent-chord flap-type controls of various spans. The wing of the semispan fuselage-wing combination had 45 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 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 written by Boyd C. Myers and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Low speed Lateral control Investigation of a Flap type Spoiler Aileron with and Without a Deflector and Slot on a 6 percent thick Tapered 45 Degree Sweptback Wing of Aspect Ratio 4 written by James M. Watson and published by . This book was released on 1952 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 300 MPH 7- by 10-foot tunnel to determine the lateral control characteristics of a deflector and slot arrangement in conjunction with a flap-type spoiler aileron. The wing had a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free air stream.

Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees Aspect Ratio 4 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and a wing-fuselage combination employing a wing with the quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for the wing-alone and wing-body configurations. 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 publishing of these data, only a brief analysis is included.

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 Transonic Wind tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing body Combination of Aspect Ratio 4 and Taper Ratio 0 6 written by Robert J. Platt and published by . This book was released on 1955 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.

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 Aerodynamic Characteristics of a Spoiler slot deflector Control on a 45 Sweptback Wing at Mach Numbers of 1 61 and 2 01 written by Douglas R. Lord and published by . This book was released on 1957 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.

Download or read book The Effect at High Subsonic Speeds of a Flap type Aileron on the Chordwise Pressure Distribution Near Midsemispan of a Tapered 35 Degree Sweptback Wing of Aspect Ratio 4 Having NACA 65A006 written by Homer B. Wilson and published by . This book was released on 1953 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents effects of the deflection of a flat-type aileron on the chordwise pressure distribution at the 46-percent-semispan station of a tapered 35 degree sweptback wing of aspect ratio 4 with an NACA 65A006 airfoil section. The tests were made at angles of attack from 0 to 20 degrees and at Mach numbers from 0.60 to 0.95 for aileron deflections from -30 to 30 degrees.

Download or read book Wind tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 and at High Subsonic Mach Numbers Including a Semiempirical Method of Estimating the Rolling Derivatives written by James W. Wiggins and published by . This book was released on 1954 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.

Download or read book Aerodynamic Characteristics of a Wing with Unswept Quarter chord Line Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A004 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1950 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing alone and a wing-fuselage combination employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. Effective downwash angles and dynamic-pressure characteristics were also obtained for these configurations for a range of tail heights in the region of a probable tail location. In order to expedite the publication of these data, only a brief analysis is included.

Download or read book Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0 6 written by George W. Jones and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.