Aerodynamic Characteristics Of A Leading Edge Slat On A 35 Degree Swept Back Wing For Mach Numbers From 030 To 088 PDF Download
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| Author | : John A. Kelly |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1951 |
| Genre | : Aerodynamic load |
| ISBN | : |
Download Aerodynamic Characteristics of a Leading-edge Slat on a 35 Degree Swept-back Wing for Mach Numbers from 0.30 to 0.88 Book in PDF, ePub and Kindle
The data presented in this report were obtained by North American Aviation, Inc., from an investigation conducted in the Southern California Cooperative Wind Tunnel. Tests were made over a range of Mach numbers from 0.300 to 0.883 to determine the aerodynamic characteristics of a semispan model of a 35 degree swept-back wing equipped with a leading-edge slat and to gain additional knowledge of the aerodynamic loads and automatic operation of the slat. Lift, drag, and pitching-moment characteristics of a model wing in the presence of a fuselage were measured as well as pressures acting on the slat in the retracted and the full-open positions. The pressure data were analyzed to ascertain the opening characteristics of the slat for two possible circular-arc slat tracks which could be used for automatic operation of the slat.
| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1961 |
| Genre | : Airplanes |
| ISBN | : |
Download Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45 Degree Sweptback Wing at Transonic Speeds Book in PDF, ePub and Kindle
| Author | : Donald D. Arabian |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1954 |
| Genre | : Airplanes |
| ISBN | : |
Download Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45© Sweptback Wing at Transonic Speeds Book in PDF, ePub and Kindle
| Author | : William C. Sleeman |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1949 |
| Genre | : Aerofoils |
| ISBN | : |
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.
| Author | : Jones F. Cahill |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1952 |
| Genre | : |
| ISBN | : |
Download Aerodynamic Load Measurements Over a Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers from 0.10 to 0.91 Book in PDF, ePub and Kindle
| Author | : Kenneth P. Spreemann |
| Publisher | : |
| Total Pages | : 644 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
Download 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 Book in PDF, ePub and Kindle
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.
| Author | : Earl D. Knechtel |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
Download 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 Book in PDF, ePub and Kindle
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.
| Author | : Jack F. Runckel |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1953 |
| Genre | : |
| ISBN | : |
Download Effects of Leading-edge Slats on the Aerodynamic Characteristics of a 45 Degree Sweepback Wing-fuselage Configuration at Mach Numbers of 0.4 to 1.03 Book in PDF, ePub and Kindle
| Author | : Jones F. Cahill |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1951 |
| Genre | : Aerodynamic load |
| ISBN | : |
Download Pressure Distributions Over a Retracted Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers Up to 0.9 Book in PDF, ePub and Kindle
Pressure distributions over a retracted leading-edge slat on a 40 degree sweptback wing are presented for a series of angles of attack up to maximum lift at Mach numbers of 0.1, 0.4, 0.6, 0.7, 0.8, 0.85, and 0.9. These data were obtained in the Langley low-turbulence pressure tunnel at a constant Reynolds number of approximately 3,000,000. The Reynolds number was maintained approximately constant through the Mach number range by varying the stagnation pressure.
| Author | : Kenneth P. Spreemann |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1957 |
| Genre | : Airplanes |
| ISBN | : |
Download 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 Book in PDF, ePub and Kindle
