Low-Speed Wind-Tunnel Tests on some Slender Airbus Configurations
نویسنده
چکیده
An experimentalinvestigation has been made of the subsonic lift, drag and longitudinal stability characteristics of models representing some alternative slender airbus configurations. For the same wing planform of aspect ratio 1.4 the lift, drag and pitching moment have been measured for two wings of maximum thickness/chord ratio 4 and 9 per cent respectively, both without and with various body arrangements. Trailing-edge controls were cut on the 4 per cent wing and the results have been used to compare trimmed lift and drag coefficients for several alternative aircraft layouts. Included are the results of some tests with a foreplane which showed that considerable gains in usable lift coefficient and lift-drag ratio could be obtained with a high-foreplane low-wing configuration.
منابع مشابه
Evaluation of salt dust occurrence potential in the North east Zone of Urmia Lake
Extended abstract 1- Introduction Urmia Lake as the largest domestic lake in Iran is drying. Climate change in the northwest of Iran, rainfall reduction and evaporation, due to the increase in average temperature in the Northwest of the country accompanied with the involvement of human factors such as dam construction, have caused an irreparable environmental hazard in the northwestern of Ira...
متن کاملExperimental Investigation of Asymmetry of Vortex Flow Over Single Delta Wings
It is generally believed that, on slender delta wings, there is a critical state at which strong asymmetric vortices are found along the leading edge on the lee-side of the delta wing. These asymmetric vortices can lead to high lateral forces even when slender delta wing is at the zero angle of yaw. Some experimental studies reported recently, cast considerable doubt as to the validity of the a...
متن کاملEffect of plasma actuation on asymmetric vortex flow over a slender conical forebody
The active flow control technology by using plasma actuation to manipulate forebody vortices on a slender conical body is being studied based on the previous research. This work is motivated by the need to increase the experimental velocity in the wind tunnel via an effective streamlining created by the actuators. A pair of Single-Dielectric Barrier Discharge (SDBD) plasma actuators is installe...
متن کاملEffect of Wing Sweep Angle on the Vortex Interaction of a Tail-Wing Configuration
The goal of this investigation is to study the effect of wing sweep angle on the horizontal wing-body- tail configurations in subsonic flow. For this purpose, a series of wind tunnel tests were conducted on a model having a moveable horizontal tail and a wing planform with different sweep angles. Tests were performed at different tail deflection angles. Static surface pressure distribution over...
متن کاملSmall Propeller and Rotor Testing Capabilities of the NASA Langley Low Speed Aeroacoustic Wind Tunnel
The Low Speed Aeroacoustic Wind Tunnel (LSAWT) at NASA Langley Research Center has recently undergone a configuration change. This change incorporates an inlet nozzle extension meant to serve the dual purposes of achieving lower freestream velocities as well as a larger core flow region. The LSAWT, part of the NASA Langley Jet Noise Laboratory, had historically been utilized to simulate realist...
متن کامل