Lanterna Rally
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Investigation of the Aerodynamic Characteristics of a 0.067-scale Model of the X-15 Airplane /configuration 3/ at Mach Numbers of 2.29, 2.98, and 4.65
Low-Speed Aerodynamic Characteristics of a Model of a Hypersonic Research Airplane at Angles of Attack Up to 90 Deg for a Range of Reynolds Numbers
Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches
Author: Charles F. Whitcomb
Publisher:
Published: 1956
Total Pages: 34
ISBN-13:
DOWNLOAD EBOOK →An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Unpowered Aerodynamic Characteristics of a 15-percent Scale Model of a Twin-engine Commuter Aircraft
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 35©, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45© Sweptback Wing at Mach Numbers of 1.61 and 2.01
Author: Douglas R. Lord
Publisher:
Published: 1957
Total Pages: 52
ISBN-13:
DOWNLOAD EBOOK →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.
Low Speed Aerodynamic Characteristics of an 0.075-scale F-15 Airplane Model at High Angles of Attack and Sideslip
Aerodynamic Characteristics of a Leading-edge Slat on a 35 Degree Swept-back Wing for Mach Numbers from 0.30 to 0.88
Author: John A. Kelly
Publisher:
Published: 1951
Total Pages: 56
ISBN-13:
DOWNLOAD EBOOK →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.
Low Speed Aerodynamic Characteristics of a Large-scale Model with a Thin, Highly Swept, 2.67 Aspect Ratio Wing Having a Cranked Leading Edge
Author: Demo J. Giulianetti
Publisher:
Published: 1972
Total Pages: 52
ISBN-13:
DOWNLOAD EBOOK →The low speed aerodynamic characteristics of a large-scale model intended to represent advanced fixed-wing fighters have been investigated in the Ames 40 by 80 foot wind tunnel. The model possessed positive static longitudinal stability to nearly 28 deg angle of attack, the maximum tested, both with and without leading-edge flaps deflected. Lateral control with differentially deflected ailerons and a right wing spoiler simultaneously deployed as combined controls was only slightly greater than that with the differentially deflected ailerons deployed as a separate control without the spoiler. Measured lift and drag were in close agreement with that predicted by theory to about 14 deg angle of attack, including the prediction of lift due to 30 deg of trailing edge flap deflection. Estimated takeoff performance of an aircraft 4/3 the scale of the test model showed takeoff distances of less than 2000 ft.
