455 research outputs found
Aerodynamic characteristics of an F-8 aircraft configuration with a variable camber wing at Mach numbers from 0.70 to 1.15
A 0.1-scale model of an F-8 aircraft was tested in the Ames 14-Foot Transonic Wind Tunnel at Mach numbers from 0.7 to 1.15. Angle of attack was varied from -2 deg. to 22 deg. at sideslip angles of 0 deg and -5 deg. Reynolds number, dictated by the atmospheric stagnation pressure, varied with Mach number from 3.4 to 4.0 million based on mean aerodynamic chord. The model was configured with a wing designed to simulate the downward deflection of the leading and trailing edges of an advanced-technology-conformal-variable camber wing. This wing was also equipped with conventional (simple hinge) flaps. In addition, the model was tested with the basic F-8 wing to provide a reference for extrapolating to flight data. In general, at all Mach numbers the use of conformal flap deflections at both the leading edge and trailing edge resulted in slightly higher maximum lift coefficients and lower drag coefficients than with the use of simple hinge flaps. There were also found to be small improvements in the pitching-moment characteristics with the use of conformal flaps
Aerodynamic characteristics of an F-8 aircraft configuration with a variable camber wing at Mach numbers from 1.5 to 2.0
A 0.1-scale model of an F-8 aircraft was tested over a range of Mach numbers from 1.5 to 2.0. Reynolds number of 4.12 million was based on wing mean-aerodynamic chord for angles of attack varying from -2 deg to +12 deg. The model was equipped with an advanced-technology-conformal-variable-camber wing (ATCVCW) having simple hinge flaps. Data were also obtained for the model equipped with the basic F-8 wing and conventional flaps. Model variables included aileron and wing trailing edge deflections and horizontal tail incidence. The ATCVCW configuration produced slight improvements in lift-curve slope, drag, and static longitudinal stability over that of the basic F-8 wing configuration. Flap effectiveness was essentially the same for both wings
Relation of phosphorus and nitrogen in soil to the composition of wheat
Cover title.Mode of access: Internet
Sulphur in relation to soils and crops
Cover title.Bibliography: p. 255-256.Mode of access: Internet
The forces and pressure distribution at subsonic speeds on a plane wing having 45 degrees of sweepback, an aspect ratio of 3, and a taper ratio of 0.5
An Analysis of the Forces and Pressure Distribution on a Wing with the Leading Edge Swept Back 37.25 Degrees
Pressure Distribution at Mach Numbers up to 0.90 on a Cambered and Twisted Wing Having 40 Degrees of Sweepback and an Aspect Ratio of 10, Including the Effects of Fences
Wind-tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds
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