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Calculation of the Aerodynamic Loading of Flexible Wings of Arbitrary Plan Form and Stiffness
A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of wings and tail surfaces of arbitrary plan form and stiffness. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included.
Introduction to Aircraft Aeroelasticity and Loads
Introduction to Aircraft Aeroelasticity and Loads, SecondEdition is an updated new edition offering comprehensivecoverage of the main principles of aircraft aeroelasticity andloads. For ease of reference, the book is divided into three partsand begins by reviewing the underlying disciplines of vibrations,aerodynamics, loads and control, and then goes on to describesimplified models to illustrate aeroelastic behaviour and aircraftresponse and loads for the flexible aircraft before introducingsome more advanced methodologies. Finally, it explains howindustrial certification requirements for aeroelasticity and loadsmay be met and relates these to the earlier theoretical approachesused. Key feat...
The Aerodynamics of a Container Freight Train
This outstanding thesis characterises the aerodynamic flow around a container freight train; investigating how changing container loading configurations affect the magnitude of aerodynamic forces measured on a container. 1/25th scale moving-model freight train experiments were carried out at the University of Birmingham’s TRAIN rig facility to investigate slipstream velocities and static pressure, as well as measuring, using a specifically designed on-board pressure monitoring system, the aerodynamic loads on containers. Results were compared with full scale data and assessed in terms European standards for trackside worker and passenger safety limits. Rail vehicle aerodynamic studies have tended to previously focus on high speed passenger trains in line with increases in train speed. The research presented within this thesis highlights the issues associated with the aerodynamic development around a freight train, providing the foundations for further research and a basis from which to develop international safety standards in relation to freight, as well as high speed trains.
Some Notes on the Aerodynamic Loads Associated with External-store Installations
The results presented in this paper indicate that the effects of stores on wing load distribution at subsonic speeds may be predicted by available methods at the lower angles of attack where wing flow separation is negligible. At the higher angles of attack where wing flow separation exists, a store located inboard on a swept wing may act much like various devices designed to delay wing pitch-up by reducing the loss in load at the wing tip due to flow separation. Furthermore, the results indicate that the normal force and pitching moment of a store located at the wing tip can be calculated quite well by available methods. On the other hand, no theoretical procedure is available to calculate the severe lateral forces and moments encountered at zero sideslip on an inboard arrangement of stores on a swept wing.
Flight Measurements of Aerodynamic Loads on the Horizontal Tail Surface of a Fighter-type Airplane
A series of flight measurements of the loads applied to the horizontal tail surfaces of a fighter-type airplane were made. The results were analyzed and found to verify the fact that a knowledge of the tail-load parameters will permit the calculation of the horizontal-tail load. The influence of sideslip on the horizontal-tail load was determined and the critical conditions for design are enumerated.
Influences of Sting Support on Aerodynamic Loads Acting on Captive Store Models
In a series of wind tunnel tests, measurements were made of the aerodynamic loads acting on eight different store configurations mounted in the external captive position on a one-twentieth-scale model of the F-4C aircraft. Store models included blunt and contoured afterbody shapes, stable and unstable designs, and large (one per pylon) and small (rack-mounted) configurations. The tests were conducted in an effort to evaluate sting effects on captive store loads. Sting effects were considered to consist of two contributions: the effect of altering the afterbody of a store to allow insertion of a sting, and the effect of the presence of the sting. Altering the afterbody of an unstable store influenced captive loads less than altering a stable configuration. It was also determined that the presence of a sting affected most the pitching and yawing moments.
Initial Experimental Investigation of the Aerodynamic Load on the Wing of a Model Caused by a Blast-induced Gust that Increases the Angle of Attack Into the Stall Region
An initial experimental investigation has been completed on the aerodynamic load imposed on the wing of an airplane model by a blast-induced gust which increased the angle of attack well beyond the stall angle. Pressure distributions at intervals of 1 millisecond were derived along the wing chord. Comparison of these distributions with distributions obtained from steady-flow wind-tunnel tests and potential-flow calculations showed that neither of the latter methods was adequate to predict the loads in the transient conditions of the blast. A traveling peak of negative pressure was disclosed that is believed to be of significance for the high angle-of-attack case. It was attributed to a vortex formed by the diffraction of the blast wave around the wing. The normal-force coefficients obtained from the flight pressure distributions were approximately twice those predicted from wind-tunnel tests for the first 12 milliseconds after blast arrival or for about 75 percent of the time the angle of attack was above the stall.
