Effect Of Longitudinal Wings Position On The Pressure Characteristics At Transonic Speeds Of A 45c Sweptback Wing Fuselage Model PDF Download
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| 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 | : |
| Publisher | : |
| Total Pages | : 104 |
| Release | : 1961 |
| Genre | : |
| ISBN | : |
Download Longitudinal Aerodynamic Characteristics at Transonic Speeds of Two V/STOL Airplane Configurations with Skewed and Variable-sweep Wings 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 | : Ralph P. Bielat |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1951 |
| Genre | : Aerodynamics, Transonic |
| ISBN | : |
Download An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47© Sweepback, Aspect Ratio 3.5, and Taper Ratio 0.2 in the Slotted Test Section of the Langley 8-foot High-speed Tunnel Book in PDF, ePub and Kindle
Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.
| Author | : Chris C. Critzos |
| Publisher | : |
| Total Pages | : 20 |
| Release | : 1956 |
| Genre | : Airplanes |
| ISBN | : |
Download A Transonic Investigation of the Static Longitudinal-stability Characteristics of a 45 Degree Sweptback Wing-fuselage Combination with and Without Horizontal Tail Book in PDF, ePub and Kindle
An investigation of the static longitudinal-stability characteristics of a 45 degree sweptback wing-fuselage configuration has been conducted in the Langley 16-foot transonic tunnel. The wing had an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections parallel to the plane of symmetry. Data were obtained for the model with and with a sweptback horizontal tail for an angle-of-attack range from -4 to about 27 degrees and for Mach numbers ranging from 0.80 to 1.05. The Reynolds number varied from 6,000,000 to about 8,500,000.
| Author | : Richard T. Whitcomb |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1952 |
| Genre | : Aerodynamics |
| ISBN | : |
Download A Study of the Flow Over a 45° Sweptback Wing -fuselage Combination at Transonic Mach Numbers Book in PDF, ePub and Kindle
Abstract: Pressure distributions, tuft patterns, and schlieren surveys have been obtained for a 45° sweptback wing-fuselage combination in the Langley 8-foot transonic tunnel at transonic Mach numbers to 1.11 and angles of attack to 20°. The results provide an indication at transonic Mach numbers of the nature of the formation of shock waves on the wing and fuselage, wing-fuselage interference, and the development of separation and the separation vortex.
| Author | : |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1964 |
| Genre | : |
| ISBN | : |
Download Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Fighter Model Having Body-mounted Nacelles Book in PDF, ePub and Kindle
| Author | : Arvo A. Luoma |
| Publisher | : |
| Total Pages | : 134 |
| Release | : 1950 |
| Genre | : Airplanes |
| ISBN | : |
Download Longitudinal Stability and Control Characteristics at High Subsonic Speeds of Two Models of a Transonic Research Airplane with Wings and Horizontal Tails of Aspect Ratios 4.2 and 2 Book in PDF, ePub and Kindle
An investigation was made in the Langley 8-foot high-speed tunnel of two transonic research airplane models for Mach numbers up to approximately 0.95. The test Reynolds number at the highest speed was 1,600,000 for one model and 2,300,000 for the other model. The models were 1/16-schale and were supported in the tunnel on a sting. The wing and horizontal tail of one model were both of aspect ratio 4.2; the wing and horizontal tail of the other model were both of aspect ratio 2. The same fuselage and vertical tail were used on both models. The sweep of the 50-percent-chord line of the wings was zero degrees; the sweep of the 75-percent-chord line of the horizontal tails was zero degrees. Both wings had NACA 65-110 airfoil sections and both horizontal tails had NACA 65-008 airfoil sections. Lift drag, and pitching moment were determined by means of a strain-gage balance within the fuselage. Tare measurements were made to eliminate the interference effect of the sting.
| Author | : Marlowe D. Cassetti |
| Publisher | : |
| Total Pages | : 104 |
| Release | : 1961 |
| Genre | : Transonic wind tunnels |
| ISBN | : |
Download Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 Book in PDF, ePub and Kindle
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
| Author | : |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1983 |
| Genre | : |
| ISBN | : |
Download Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0.25 to 4.63 Book in PDF, ePub and Kindle
