Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing
Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing

Author: Edward C. Polhamus

Publisher:

Published: 1958

Total Pages: 36

ISBN-13:

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A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.

Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6
Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6

Author: Walter P. Nelms

Publisher:

Published: 1971

Total Pages: 108

ISBN-13:

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Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers.

Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Deg Cropped Delta Wing
Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Deg Cropped Delta Wing

Author: National Aeronautics and Space Adm Nasa

Publisher:

Published: 2018-11-22

Total Pages: 176

ISBN-13: 9781731536075

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A wind tunnel data base was established for the effects of chine-like forebody strakes and Mach number on the longitudinal and lateral-directional characteristics of a generalized 55 degree cropped delta wing-fuselage-centerline vertical tail configuration. The testing was conducted in the 7- by 10-Foot Transonic Tunnel at the David Taylor Research Center at free-stream Mach numbers of 0.40 to 1.10 and Reynolds numbers based on the wing mean aerodynamic chord of 1.60 x 10(exp 6) to 2.59 x 10(exp 6). The best matrix included angles of attack from 0 degree to a maximum of 28 degree, angles of sidesip of 0, +5, and -5 degrees, and wing leading-edge flat deflection angles of 0 and 30 degrees. Key flow phenomena at subsonic and transonic conditions were identified by measuring off-body flow visualization with a laser screen technique. These phenomena included coexisting and interacting vortex flows and shock waves, vortex breakdown, vortex flow interactions with the vertical tail, and vortices induced by flow separation from the hinge line of the deflected wing flap. The flow mechanisms were correlated with the longitudinal and lateral-directional aerodynamic data trends. Erickson, Gary E. and Rogers, Lawrence W. Langley Research Center AERODYNAMIC CHARACTERISTICS; DELTA WINGS; FLOW CHARACTERISTICS; FOREBODIES; LATERAL STABILITY; LONGITUDINAL STABILITY; MACH NUMBER; STRAKES; WIND TUNNEL TESTS; AIRFOIL PROFILES; ANGLE OF ATTACK; BOUNDARY LAYER SEPARATION; CHORDS (GEOMETRY); FLOW VISUALIZATION; SHOCK WAVES; VORTEX BREAKDOWN; VORTICES; WING FLAPS...

Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length
Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length

Author: Carlton S. James

Publisher:

Published: 1960

Total Pages: 42

ISBN-13:

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An aircraft configuration, previously conceived as a means to achieve favorable aerodynamic stability characteristics., high lift-drag ratio, and low heating rates at high supersonic speeds., was modified in an attempt to increase further the lift-drag ratio without adversely affecting the other desirable characteristics. The original configuration consisted of three identical triangular wing panels symmetrically disposed about an ogive-cylinder body equal in length to the root chord of the panels. This configuration was modified by altering the angular disposition of the wing panels, by reducing the area of the panel forming the vertical fin, and by reshaping the body to produce interference lift. Six-component force and moment tests of the modified configuration at combined angles of attack and sideslip were made at a Mach number of 3.3 and a Reynolds number of 5.46 million. A maximum lift-drag ratio of 6.65 (excluding base drag) was measured at a lift coefficient of 0.100 and an angle of attack of 3.60. The lift-drag ratio remained greater than 3 up to lift coefficient of 0.35. Performance estimates, which predicted a maximum lift-drag ratio for the modified configuration 27 percent greater than that of the original configuration, agreed well with experiment. The modified configuration exhibited favorable static stability characteristics within the test range. Longitudinal and directional centers of pressure were slightly aft of the respective centroids of projected plan-form and side area.