Abstract: The invention relates to a flow state sensor (10) for detecting a flow state at a body (16) that may be impinged on by a flow (12). A flow state sensor (10) that is of a simple construction and that is simple to evaluate is characterised in accordance with the invention by at least one frequency detecting device (20) for detecting at least one predefined frequency characteristic of the flow state. The frequency detecting device (20) has at least one oscillation element (22; 22a, 22b, 22c) excitable to resonant oscillatory movement (30) by a flow (12) and having a resonant frequency or natural frequency adapted to the predefined frequency characteristic, especially corresponding to the predefined frequency characteristic. Uses of the flow state sensor (10) in a flow measuring device (62) and in a flow measuring method, and an advantageous production method for the flow state sensor (10) are also proposed.

Abstract: Provided is a compact wind tunnel instrument. The compact wind tunnel instrument includes a blowing unit configured by a plurality of blowing devices provided in the same plane, and a control unit for controlling them, thereby easily providing a variety of wind environments.

Abstract: A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft.

Abstract: The invention is directed to a wind tunnel designed to operate along a vertical section such that air currents, generated by appropriate fans, meet in a vertical area wherein the air currents are capable of lifting objects in this vertical area. the lifting effect may be seen on the outside of the wind tunnel as the tunnel is built from translucent materials. The viewing and lifting of bodies in the vertical section of the tunnel allows both their display and for measurements to be taken of the bodies.

Abstract: An aerodynamic test stand (1) is provided for determining forces acting on a vehicle. The test stand has a stationary floor (2), at least two supporting devices (4) for supporting the motor vehicle, and at least one band unit moving in relation to the floor, for influencing air flow behavior in the floor region. The band unit is composed, segment-like, of runway sections (9, 10, 11, 20, 21, 22, 23, 24, 25, 26, 27, 28) to accurately detect forces acting on the vehicle.

Abstract: A system for resolving the measured forces and moments at VRS attachment points and tire contact patches to a standard format for a wheeled vehicle in a windtunnel. The system reduces the data to arrive at the aerodynamic forces, moments and coefficients. The test vehicle is equipped with one or more wheel force transducers installed between the wheels and the corresponding hubs. A VRS rod or strut attaches to the wheel so that loads through the hub and into the wheel are sensed at both the VRS strut and the tire contact patch. The force transmitted through the hub into the wheel is sensed and measured directly by the wheel force transducer. The combination of measurements from the VRS load cells and the wheel transducers allows the determination of the external forces acting on the vehicle at the tire contact patch, which in turn leads to the aerodynamic forces acting on the vehicle. When combined with the geometry of the vehicle, the aerodynamic moments acting on the vehicle can then be determined.

Abstract: A system for simulating the ground effect for testing vehicles or their simulacra in wind tunnels includes a resting surface for the vehicle incorporating a moving belt for simulation of the ground, extending between the wheels of the vehicle, at least from one end to the other of the vehicle, as well as two auxiliary moving belts set immediately adjacent to the two sides of the front portion of the main moving belt, for simulating the ground in areas in front of the front wheels of the vehicle.

Abstract: A sports arena comprised of a vertical wind tunnel modular unit capable of conjoining with a multitude of vertical wind tunnel modular units joined in tandem for the purpose of levitating humans in a sports arena. The vertical wind tunnel sports arena is designed so that a single vertical wind tunnel modular unit can be utilized as a self contained sports arena or multiple vertical wind tunnel modular units can be combined together in tandem to form an expansive arena where various competitive sports can be played while the athletes are levitating in mid air. The arena contains two separate target systems, each suspended twenty feet above a trampoline safety net, disposed at polar opposite ends of the sports arena. A ball striking a button in the middle of a backboard on the target system will cause a fireball or Tesla coil report to discharge indicating a field goal.

Abstract: A minimum aerodynamic interference support for models in a cryogenic wind tunnel includes two main pieces: a front sting substantially parallel to the longitudinal axis of the model and a blade, integrated together and describing an obtuse angle. The support is connected to the model by means of the blade, being the model such that it emulates a tail section and/or wings of an aircraft. The front sting of the support comprises an extension, extended horizontally underneath a frontal zone of the fuselage of the model, starting from the point where the blade starts and extending past the point where the blade is connected to the model, in such a way that the length and area dimensions of the cross-section of the extension are obtained by applying the aerodynamic principle, area rule, to the ensemble made up by the front sting, the blade, the model and the extension.

Abstract: An aerodynamic hood lift deflection measurement device includes an airfoil body mounted to a front vehicle fender such that a portion of the airfoil body held over the vehicle hood. A laser measurement device is secured to the airfoil body in a position so as to be directly over the vehicle hood. The airfoil body is mounted at an angle such that a length direction of the airfoil body is parallel to an air flow direction. The resultant disruption of the air flow surrounding the vehicle hood is minimized due to the shape and positioning of the measurement device.

Abstract: A method is disclosed of identifying or fixing the value of the parameters (aerodynamic data) of a pre-determined set of equations forming the aerodynamic models of an aircraft in various configurations, so as to minimize the variance between the values anticipated by using these aerodynamic data, and reference data in cases of known configurations, includes the use of learning or optimization methods to determine at least one portion of the parameters' values. The method includes storing database data, choosing an optimization method or a neural network method, breaking the identification down into several partial identifications, carrying out successive partial identifications, validating the values found for the aerodynamic model's parameters or iterating the method according to a threshold criterion determined on the value of variances between the reference data and the values measured by the identified model.

Abstract: A system for measuring a multiplicity of pressures as those experienced by a model in a wind tunnel is depicted. The system includes individual sensor devices which are connected to an Acquisition and Compensation electronics module. The individual sensor or transducer devices are semiconductor piezoresistive devices and are connected to the Acquisition and Compensation electronics module by means of a cable in a first embodiment. In an alternate embodiment the system uses connectors which connect each of the individual sensor devices to the Acquisition and Compensation electronics module via a mating connector located therein. The connectors may also include a memory which stores compensation coefficients associated with each of the various sensor devices. In this manner as described, the transducers which are small devices are connected via electrical lines or cables to the central Acquisition and Compensation electronics modules.

Abstract: Provided is a test section for a wind-tunnel testing apparatus that is capable of suppressing the influences of a boundary layer on the floor surface and incoming airflows from the sides, and that is capable of measuring aerodynamic forces closer to the those actually occurring. A test section for a wind-tunnel testing apparatus having a mounting section that mounts an automobile along the internal floor surface of a wind tunnel, tests being conducted by applying an airflow blown in the wind tunnel to the automobile mounted on the mounting section, includes a slit that is disposed on the floor surface located on the upstream side of the mounting section with respect to the airflow direction so as to extend in the intersecting direction intersecting the airflow direction and that sucks in a portion of the airflow near the floor surface; and lateral suction portions, disposed at both sides of the mounting section, that suck in the incoming airflows R flowing in from the sides of the mounting section.

Abstract: A system for simulating the ground effect for testing vehicles or their simulacra in wind tunnels includes a resting surface for the vehicle incorporating a moving belt for simulation of the ground, extending between the wheels of the vehicle, at least from one end to the other of the vehicle, as well as two auxiliary moving belts set immediately adjacent to the two sides of the front portion of the main moving belt, for simulating the ground in areas in front of the front wheels of the vehicle.

Abstract: In order to discriminate between laminar flow and turbulent flow states, and to provide an indication, e.g. to a pilot of an aircraft of air flow over an aircraft wing, a sensor mounted on the wing provides an analogue signal of airflow, and an intermittency value of the analogue signal is derived in analogue circuitry including an AC coupling of the signal to an integrator for integrating the signal for a preset time. The integrated value is compared with a threshold value to indicate whether the intermittency represents quiet laminar flow or noisy turbulent flow.

Abstract: The invention relates to a probe for aerodynamic measurement of an airflow. The probe comprises a plate rotating about an axis, a transmitter for transmitting a sound wave and a receiver responsive to the sound wave, the transmitter and the receiver forming two elements which are integrally connected to the plate and are placed at separate positions on the plate, the probe furthermore comprising means for delivering information representing a time of flight of the sound wave between the two elements and a temporal variation of the information. In the case of using the probe on board a helicopter, the rotating plate is advantageously placed at the centre of the rotor of the helicopter while being integrally connected to it. This type of probe makes it possible to carry out aerodynamic measurements even at low airspeeds of the helicopter.

Abstract: There is disclosed a current tank system comprising a first current tank adapted to produce a first current in a first direction, and a second current tank adapted to produce a second current in a second direction. There is also disclosed a method of testing a sample, comprising exposing the sample to a first current in a first current tank, and exposing the sample to a second current in a second current tank.

Abstract: Apparatus and method for visualizing air stream by little threads on aerodynamic surfaces such that strips of adhesive tape populated with threads are automatically fabricated.

Abstract: A wind tunnel testing technique or method involves using feedback to position control surfaces of a model so that there is substantially no moment on the model for its given orientation to the airstream. The model is mounted on a sting that allows change in orientation of the model relative to the airstream. A balance is used to provide data regarding the forces and/or moments on the model. This data on forces and/or moments is used in one or more feedback loops to position the control surfaces of the model so that there are substantially no moments on the model. This may be done automatically, with a controller automatically controlling the position of the control surfaces to zero out the moments on the model. The use of the method may allow faster determination of model characteristics, such as determination of the trim envelope of the model.

Abstract: A system for setting a spatial position of a vehicle relative to a foundation, on which the vehicle is standing with its wheels, in particular in a wind tunnel, is provided. The adjusting system includes a plurality of linear actuating devices, which are assigned to each one of the wheels and which are mounted on the vehicle in the area of the respective wheel and with which in the area of the respective wheel a distance between the foundation and a vehicle chassis can be set. The adjusting system includes a plurality of measuring devices, which are assigned to each one of the actuating devices, for determining the distance between the foundation and the vehicle chassis in the area of the respective wheel.

Abstract: Methods and systems providing for characterizing turbine blades, including characterizing the dynamics of one or more turbine blades or stages of a stage in terms of natural frequencies, normalized response intensity, and/or stage modal shape or nodal configuration. Such methods and systems comprise fluid (e.g., oil) excitation of bladed disks and quantitative modeling of the fluid excitation. Additionally or alternatively, such methods and systems may provide for analyzing modal shape or nodal configuration of a bladed disk (e.g., a turbine stage) based on a phase analysis of strain signals acquired from a bladed disk subjected to a fluid excitation, wherein the modal shape or nodal configuration corresponds to modes of blades coupled through a disc or shrouding.

Abstract: The present invention relates to a method and a measuring device for measuring and displaying the overlap between a rear edge of an aircraft wing and a front edge of a landing flap fixed thereto. In accordance with the invention, only the difference in the positions of the rear edge of the aircraft wing and the front edge of the landing flap relative to the longitudinal direction of the aircraft is determined. For this purpose, a first sensor is positioned, as a reference of sorts, at one of the two positions, for example at the rear edge of the aircraft wing, and the display is then reset to zero or to another reference value. By positioning the second sensor, which is also rigidly connected to the calliper, at the other respective position, for example at the front edge of the landing flap, the difference between the front edge of the landing flap relative to the rear edge of the aircraft wing is established.

Abstract: A device for evaluating a wind tunnel measurement, in which a processor identifies a flow element on an image recorded in the wind tunnel. The identified flow element subsequently may be segmented and further analyzed in order to obtain accurate information about the flow behaviour of an object to be analyzed. In addition, a method, a computer-readable storage medium, a program element, and an arrangement are disclosed.

Abstract: A closed loop control system for controlling an actuator operating on a moveable member, includes a control device controlling operation of the actuator, a sensor responsive to a condition such as loading of the moveable member as it is moved by the actuator and adapted to generate a corresponding feedback control signal SL, and a damping device having a damping effect on the response of the actuator to the feedback control signal, the damping effect being varied in accordance with the movement of the moveable member so as to vary the response of the actuator. The damping effect is increased in the region of stationary states to render the system more stable, and reduced therebetween to make the system more responsive at increased speeds, and thereby more conformal to a required performance profile. The position or velocity of the moveable member can be used to control the damping effect, or a timer can be used to control the damping effect.

Abstract: The invention relates to closed-circuit tunnels used for aerodynamic researches, sportsmen-parachutists training and other purposes. The inventive closed-circuit tunnel comprises a confuser, a working area, a diffuser, one or several return channels, a blower unit and turning bends having different flow deflection angle, wherein the bend having the smaller flow deflection angle is placed in a high-speed flow cross-section, whereas the bend having the greater flow deflection angle is arranged in a low flow speed cross-section. In a preferred embodiment, the tunnel comprises a first turning bend containing one turning gut for turning the airflow at 60 degrees, a second turning bend containing two turning guts for turning the airflow at 120 degrees, and a third turning bend containing three turning guts for turning the airflow at 180 degrees. The invention makes it possible to reduce air pressure losses, the drive power and a specific amount of metal per structure.

Abstract: A wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, wherein the wind tunnel comprises at least one computer unit and at least one visual display terminal particularly at least one monitor, as well as at least one sensor for acquiring the measuring data. A plurality of measuring data of the wind tunnel, particularly measuring data on flow and/or pressure conditions on the model and/or in the region of the model, which data are determinable by the at least one sensor, can be processed in real time and with consideration of geometrical data of the model by the at least one computer unit and visualized on the at least one visual display terminal during a wind tunnel measurement.

Abstract: A fasten device for tire pressure alarm transmitter, which comprises a fasten base for fastening a valve core style transmitter, and a strip for binding the fasten base on wheel rim, wherein: the fasten base has a board shaped support portion, and a hole for accepting the strip to drill through is set on the support portion; a securing board is set on the middle portion of the support portion, and a position slot that matches with the valve core of the transmitter is excavated on the securing board; and a buckle that matches with the securing board is set on one end of the support portion to fasten the transmitter corporately. As the fasten base having a support portion, a buckle and a securing board with position slot are provided on the support portion.

Abstract: A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft.

Abstract: A method for modeling the acoustic signature produced by an aircraft of interest flying at a particular supersonic Mach number/altitude operating point of interest. The method includes operating a sub-scale aircraft that is a sub-scale version of the aircraft of interest at a supersonic Mach number and at an altitude that are respectively different from the Mach number and the altitude associated with the operating point of interest. The Mach number and altitude at which the sub-scale aircraft is operated is selected such that peak overpressure generated by the sub-scale aircraft and time to rise to peak overpressure are the same as peak overpressure and time to rise to peak overpressure caused by operating the aircraft of interest at the operating point of interest.

Abstract: A vehicle excitation testing system and method can include a device for simulating a vehicular motion and vehicular vibration and then measuring response. The system is designed to test front and/or rear wheel sections of a vehicle. The testing system can include a vehicle suspension system including a wheel and chassis, an excitation actuator connected to the suspension system, and a dummy or a real vehicle body linked to the suspension system and having a frame. The frame can be positively attached to the ground surface or floor or other similar isolated and stable base surface. Measuring devices can be connected to the frame, suspension and/or wheels. When the vehicle is excited to simulate road and other conditions, the wheels, suspension system and the vehicle body vibrate. Measurement of these transmitted vibrations can be studied in order to determine how to best control unwanted or unnecessary vibrations in the vehicle.

Abstract: The invention relates to closed-circuit tunnels used for aerodynamic researches, sportsmen-parachutists training and other purposes. The inventive closed-circuit tunnel comprises a confuser, a working area, a diffuser, one or several return channels, a blower unit and turning bends having different flow deflection angle, wherein the bend having the smaller flow deflection angle is placed in a high-speed flow cross-section, whereas the bend having the greater flow deflection angle is arranged in a low flow speed cross-section. In a preferred embodiment, the tunnel comprises a first turning bend containing one turning gut for turning the airflow at 60 degrees, a second turning bend containing two turning guts for turning the airflow at 120 degrees, and a third turning bend containing three turning guts for turning the airflow at 180 degrees. The invention makes it possible to reduce air pressure losses, the drive power and a specific amount of metal per structure.

Abstract: A method for monitoring operating parameters of a rotating blade is provided. The blade includes at least one sensor thereon, the sensor operatively coupled to a data acquisition device. The method includes transferring data from the sensor to the data acquisition device, the data relating to blade acceleration measurements, transmitting a signal representative of the transferred data from the data acquisition device to a control system, and controlling blade loads using the transmitted signal.

Abstract: Minimum aerodynamic interference support for models in a cryogenic wind tunnel comprising two main pieces: a front sting substantially parallel to the longitudinal axis of the model and a blade, integrated together and describing an obtuse angle. The support is connected to the model by means of the blade, being the model such that it emulates a tail section and/or wings of an aircraft. The front sting of the support comprises an extension, extended horizontally underneath a frontal zone of the fuselage of the model, starting from the point where the blade starts and up to surpassing the point where the blade is connected to the model, in such a way that the length and area dimensions of the cross-section of the extension are obtained by applying the aerodynamic principle, area rule, to the ensemble made up by the front sting, the blade, the model and the extension.

Abstract: An aerodynamic hood lift deflection measurement device includes an airfoil body mounted to a front vehicle fender such that a portion of the airfoil body held over the vehicle hood. A laser measurement device is secured to the airfoil body in a position so as to be directly over the vehicle hood. The airfoil body is mounted at an angle such that a length direction of the airfoil body is parallel to an air flow direction. The resultant disruption of the air flow surrounding the vehicle hood is minimized due to the shape and positioning of the measurement device.

Abstract: A test system includes a platform having a movable endless belt. A restraint is configured to restrain a test article in a selected vertical position relative to the moveable belt. The restraint includes at least a pair of axially rigid supports wherein at least one rigid support is provided on each side of the movable belt and has an end configured to be secured to the test article, and wherein each support extends from a stationary portion, relative to the belt, of the platform over at least a portion of the movable belt.

Abstract: A structure used to raise persons by use of air jets (currents), includes several flight positions (3). Each flight position is associated with a device (1) that generates a vertical air flow, whose flow rate and intensity are constantly monitored from a control room (9) provided with an alphanumeric display. The device (1) includes a variable pitch propeller (6) driven by an electric motor whose rpm is adjusted using an inverter. An electric signal from a balance (7) is processed in order to determine what frequency the motor supply current should have to raise a participant of this weight up to a maximum height which is preferably about 2.5 to 3 meters.

Abstract: The invention refers to a wind tunnel designed to operate in its vertical section that is to say, air currents generated by appropriate means meeting in a vertical area at the end of which the air current is capable of lifting objects in this vertical area. At the same time this lifting effect may be seen on the outside as it has been built from translucent materials. The viewing and lifting of bodies in this device allows both their display and measurements to be taken.

Abstract: A vehicle supporting platform can be supported at plural locations (e.g., four locations) from below such that the platform can pivot fore to aft and side to side in response to the impact of wind on a vehicle on the platform. In a desirable form, the platform is suspended by four suspension rods or cables that loosely support the respective corners of a platform supporting structure. The platform supporting structure can be positioned in a bay beneath the floor level. Although a different number of sensors can be used, in one approach there is one aft motion sensor coupled to the front of the floor supporting frame and a wall portion of the bay and two side sensors, one adjacent to the front of the platform and the other adjacent to the rear of the platform. Both of the side sensors can be on the same side of the platform. A double ball joint can be used to couple the sensor to the structure in one embodiment to eliminate off axis loading.

Abstract: A plasma heated arcjet wind tunnel is provided with tunnel segments in the arc-constrictor. The tunnel segments are fabricated of two concentric discs, an outer disc and an inner disc, with a groove formed in an outer edge of the inner disc. The two concentric discs which fit snugly into one another and are joined at their welded interface by a straight and angled butt joint formed between an inner edge of the outer disc and an outer edge of the inner disc. The straight and angled butt joints can be welded by electron beam welding, laser welding, or friction stir welding.

Abstract: A wheel is provided for a test vehicle. The wheel has a rim and a hub, and whereby at least one force sensor is placed in the flux of force between the hub and the rim. A test stand is provided with the test vehicle that has multiple vehicle wheels and one or more of these vehicle wheels is embodied as a wheel with a force sensor placed between the hub and the rim. An appropriate procedure is provided for determining the aerodynamic characteristics of the test vehicle. Especially with a test stand equipped with a wide belt, the forces relevant to measurement of the drag coefficients can be reliably measured with the aid of the specific wheel with the force sensor. Use of overhead scales that have an undesired effect on the flow can be dispensed with.

Abstract: A system for setting a spatial position of a vehicle relative to a foundation, on which the vehicle is standing with its wheels, in particular in a wind tunnel, is provided. The adjusting system includes a plurality of linear actuating devices, which are assigned to each one of the wheels and which are mounted on the vehicle in the area of the respective wheel and with which in the area of the respective wheel a distance between the foundation and a vehicle chassis can be set. The adjusting system includes a plurality of measuring devices, which are assigned to each one of the actuating devices, for determining the distance between the foundation and the vehicle chassis in the area of the respective wheel.

Abstract: The invention disclosed herein provides a subsonic wind tunnel capable for accurately maintaining a desired Mach number, pressure and temperature for use in aerothermal testing of materials. The invention allows the Mach number to be precisely controlled in the test section of the wind tunnel by employing a restricted outlet acting as a sonic throat for the wind tunnel. In the preferred embodiment, the restricted outlet is constructed to be variable in cross sectional area allowing a range of Mach numbers to be tested. The variable outlet is varied during the operation of the wind tunnel so that an actual trajectory with changing Mach numbers, pressure, and temperature is simulated.

Abstract: The System for sealing for variable spaces comprising sealing means (3) for at least partially packing a space (4) between two pieces (1, 2) of a model, characterised in that at least a first piece (1) of the model presents, on its side facing a second piece (2) of the model, at least one recess (5) with a front end (5a) open and a back wall (5b), with the sealing means, comprising an elastic and flexible sealing body (3), being located in the front end (5a), and the back wall (5b) containing a set of spring elements (6, 7) among which are to be found coil springs or elastic strips, at least partially compressed by the sealing body (3) and which push the latter against the surface of the second piece (1b) of the model.

Abstract: A method for improving the precision of wind tunnel measurements provides a correction to reduce the influence of a suspension device. A model, such as an aircraft model, is held by the suspension device in a wind tunnel and has multiple suspension wires. By attaching one or more sleeves to each suspension wire, a plurality of measurements with identical model configuration are capable of providing data for extrapolating corrected measurement values for a plurality of aerodynamic characteristic variables measurable in a wind tunnel. Examples of sleeves include a slit along the sleeve length and an inner diameter of the sleeves selected such that the sleeve is capable of being pressed onto and removed from a suspension wire or a sleeve of lesser outer diameter.

Abstract: An apparatus and method is provided for testing at least one performance characteristic of a vehicle.

Abstract: A system is provided for controlling boundary layer shear stress adjacent a surface over which a fluid stream has been established. The system comprises a boundary layer control device adapted for altering at least one flow characteristic within a boundary layer in a selected region of the surface. The system further comprises a shear stress measurement system comprising a hot film sensor arrangement having at least one hot film sensor element appliable to the surface in the selected region. The at least one hot film sensor element is connected to an anemometer circuit configured to provide a sensor signal corresponding to heat transfer from the associated hot film sensor to the fluid stream. The system also comprises a control module in communication with the anemometer arrangement and the boundary layer control device. The control module is adapted for receiving and processing sensor signals signal from the anemometer circuit and for providing input signals to the boundary layer control device.

Abstract: Disclosed is a method of and system for gathering off-body pressure signature data from a scaled model in a wind tunnel. The data is gathered using a probe having multiple longitudinally disposed static pressure ports. Because of the number of ports and their spacing, the probe is able to remain stationary in the tunnel for the entire range of Mach numbers and model positions to be tested. Thus, tunnel flow characteristics can be easily and effectively removed. The system also has an automated model positioning system which enables settings at different pitch, yaw, and roll angles. This enables the user to locate the model so that it can be traversed at a fixed distance above the probe while maintaining the desired angular orientation of the model. By repeatedly traversing the model at different angular orientations, a detailed and accurate off-body pressure distribution can be obtained. The wind tunnel test technique captures full off-body pressure signatures in a complete 360 degree azimuthal range.

Abstract: A method for wind-noise testing of an automobile in a wind tunnel is disclosed. The method includes measuring wind-noise generated by the automobile in a first condition. The first condition is the condition of the automobile with a predefined set of exterior components attached. The method further includes measuring the wind-noise generated by the automobile in a second condition. The second condition is the condition of the automobile with all exterior components removed and all individual gaps taped. The second condition is the fully quiet condition of the automobile. The method also includes measuring the wind-noise generated by the automobile after adding a single individual exterior component and/or un-taping an individual gap.

Abstract: A method for designing aircraft including providing a model of the aircraft and a plurality of sensors mounted on the model. The method further includes positioning the aircraft model in a fluid tunnel at an initial attitude and measuring an initial orientation of the aircraft model while the aircraft model is at the initial attitude using a first tilt sensor of the sensors to create initial orientation information. The method also includes passing fluid over the aircraft model using the fluid tunnel and actively moving the aircraft model from the initial attitude to a subsequent attitude. In addition, the method includes measuring a subsequent orientation of the aircraft model while the aircraft model is at the subsequent attitude using a first orientation sensor of the sensors to create subsequent orientation information.

Abstract: A structure for reducing turbulence and increasing flow uniformity in a flowing fluid in a wind tunnel, or a fluid channel, has a plurality of conduits or channels arranged into a conduit bundle. The conduit bundle has a number of parallel conduits with plurality of perforations on the inner side walls of the conduit. As the fluid flows through the conduit bundle the sides of the conduits reduce lateral turbulence while the perforations minimize pressure gradients in the flowing fluid in adjacent conduits, resulting in isotropic turbulence. The invention is particularly useful in testing aircraft, improving engine performance, and fluid mechanics applications.