Abstract: A wind tunnel making it possible to measure the vaporization parameters of a test liquid exposed in a gas flow is disclosed. The wind tunnel comprises: a gas generator configured to generate a gas at a flow rate and at a temperature that are adjustable; a conditioning device designed to obtain a horizontal and uniform flow of the generated gas; a measurement chamber containing the liquid to be tested and various measurement devices making it possible to characterize the flow of gas passing through the measurement chamber; a tapping and analysis zone in which the gas-and-vapor mixture is tapped analyzed; and a discharge zone configured to discharge the gas-and-vapor mixture. The liquid to be tested in the tunnel presents a free surface positioned inside the measurement chamber in a manner such that it is swept continuously and tangentially by the uniform flow of gas.

Abstract: A method and apparatus for an icing simulation system. The icing simulation system comprises a wind tunnel, a nozzle system, and a controller. The nozzle system is configured to spray drops of water within the wind tunnel. The controller is configured to control a number of properties of the water in the nozzle system such that the nozzle system sprays the drops of the water with different sizes for a desired type of icing condition.

Abstract: The invention relates to a belt unit in a wind tunnel balance for motor vehicles, in particular for determining forces and moments acting on a motor vehicle in a wind tunnel, wherein an area exposed to wind is minimized by means of a trapezoidal support, which is raised with respect to a normal zero position, and appropriately adapted test stand covers. The wind-exposed area of the endless belt of the belt test stand can be reduced here to a value which is only slightly above the necessary wheel contact area (tire shuffle). As a result, error forces can be reduced further, so that the result is highly increased measurement accuracy.

Abstract: There is provided a wind tunnel model measuring system for use with a wind tunnel. The system has a measuring assembly with an automated movable structure with at least one measuring device mounted thereon and configured for placement within the wind tunnel, and a measuring controller device located outside the wind tunnel to control the automated movable structure in order to remotely move the automated movable structure from a storage position within the wind tunnel to one or more operating positions with respect to a wind tunnel model within the wind tunnel and to allow the at least one measuring device to determine a relative position of at least one movable first component with respect to a second component, both of the wind tunnel model. The system further has a processing device configured for placement outside the wind tunnel and coupled to the measuring controller device.

Abstract: A system is provided that employs a programmable computer on which a graphical user interface provides parametric design and analysis of pressure sensor arrays used in aero- or hydroacoustic investigations. Use of the system allows for scientific and parametric investigations of turbulent boundary layer physics, as well as iterative array design optimization. Additionally, the system including the graphical user interface facilitates comparison of the results of current models for wall pressure with past theoretical or experimental wall pressure.

Abstract: There is described a method for generating a parameter for airfoil performance monitoring, the method comprising: receiving at least a first signal indicative of a first airflow parameter measured at one of an aft position and a side-facing position of a sensor mast mounted to an airfoil and at least a second signal indicative of a second airflow parameter measured at a fore position of the sensor mast; generating a turbulence intensity ratio for each one of the first airflow parameter and the second airflow parameter; and combining the turbulence intensity ratio of the first airflow parameter and the turbulence intensity ratio of the second airflow parameter to generate a combined turbulence intensity ratio for airfoil performance monitoring.

Abstract: Methods and systems for optimizing the design of aerodynamic surfaces are provided. They include in the design process of an aerodynamic surface of a body which moves through a flow field, the following: preparation of a CFD simulation of said body; resolution of the CFD calculation for specific conditions of the flow field and for obtaining flow lines of the flow on said surface; calculation of at least one geometrical variable of the surface, such as, for example, the normal curvature, according to the direction of said flow lines; and simultaneous visualization of the surface of said body and of at least one geometric variable. Additionally, at least one variable of the aerodynamic flow, such as, for example, a pressure gradient, may be calculated and visualized.

Abstract: A device for adjusting the pitch angle of propeller blades for a model engine including at least one rotor, the blades extending radially on the surface of the rotor to form a propeller. It includes a tool-holder including a base designed to be fixed to a part of the outside of the engine housing and an upper part, the aforementioned upper part being fitted with means of support movable horizontally along a longitudinal axis (XX?), the aforementioned axis being parallel to the main axis of the model engine, contactless means of optical measurement, the aforementioned means of measurement being mounted on the movable means of support by using means of travel in rotation around an axis of rotation, the aforementioned axis of rotation being the blade's axis of rotation.

Abstract: A wind tunnel device defines a cyclical tunnel to receive continuous airflow. Airflow is delivered through the tunnel to a testing region that includes a first portion carrying an arm including a spray tip configured to spray particulates in the testing region at an angle, and a second portion including an enlarged cutout region configured to receive the angled sprayed particulates. As airflow carries the angled spray particulates into the second portion, the enlarged cutout region enables the spray particulates to pass through and exit the second portion of the testing region. Analysis in the second region may be conducted through transparent walls free of openings to minimize exposure of the spray particulates to the exterior of the device. A scrubber is adapted to extract spray mist from the airflow as the airflow exits the testing region and is re-circulated through the cyclical tunnel.

Abstract: A method for establishing a wind turbine generator with one or more Permanent Magnet (PM) rotors. The method comprises the steps of: manufacturing a generator prepared for taking one or more PM rotors, manufacturing one or more rotors comprising a plurality of holding means prepared for retaining PM material, mounting substantially non-magnetized PM material prepared for magnetization in said holding means before or after said one or more rotors are mounted in said generator, connecting a magnetization system for magnetizing said PM material in the generator, and magnetizing said PM material with said magnetization system. The invention also relates to a wind turbine nacelle, a wind turbine comprising said wind turbine nacelle and use of a wind turbine.

Abstract: A probe for measuring a local angle of attack designed to be fixed to a wall and a method implementing the probe are provided. The probe comprises at least three pressure sampling ports disposed over a nose of the probe body, pressure measurement means associated with the pressure sampling ports and calculation means capable of determining an angle of attack of the flow with respect to the main direction of the probe body as a function of the pressures measured by the pressure measurement means. The calculation means are configured for choosing from amongst the pressure sampling ports those allowing the best measurement precision of the local angle of attack to be obtained and for calculating the local angle of attack with respect to the main direction using the pressure measurements carried out in the chosen pressure sampling ports.

Abstract: An aircraft model for testing in a wind tunnel of width W including a fuselage, a truncated wing whose length L1 is less than the length L of a full scaled wing and additional components in the rear of the aircraft as, in particular, a horizontal tail plane, that produces the same downwash that arrives to the additional components as in a full scaled model. The shape of the truncated wing may be designed for having a similar lift distribution to the lift distribution of a full scaled wing along at least the maximum length L2 in the Y-axis of any component in the rear of the aircraft. The invention also relates to a method for designing the truncated wing.

Abstract: A system is provided for transmitting data between a first component and a second component, which rotates relative to the first component. The system includes a first coupling element of limited angular extent mounted to the first component, and a second coupling element of limited angular extent mounted to the second component. The first and second coupling elements come into angular alignment once per revolution of the second component relative to the first component. The system further includes a first transceiver connected to the first coupling element, and a second transceiver connected to the second coupling element. The first and second transceivers are configured to detect the angular alignment of the first and second coupling elements. The first and second transceivers are further configured to transmit data between the first and second transceivers via the first and second coupling elements when the angular alignment is detected.

Abstract: This invention is a ground flutter testing system without a wind tunnel, called Dry Wind Tunnel (DWT) System. The DWT system consists of a Ground Vibration Test (GVT) hardware system, a multiple input multiple output (MIMO) force controller software, and a real-time unsteady aerodynamic force generation software, that is developed from an aerodynamic reduced order model (ROM). The ground flutter test using the DWT System operates on a real structural model, therefore no scaled-down structural model, which is required by the conventional wind tunnel flutter test, is involved. Furthermore, the impact of the structural nonlinearities on the aeroelastic stability can be included automatically. Moreover, the aeroservoelastic characteristics of the aircraft can be easily measured by simply including the flight control system in-the-loop. In addition, the unsteady aerodynamics generated computationally is interference-free from the wind tunnel walls.

Abstract: A piezoresistive sensor assembly is provided that has a flex circuit having at least one air flow aperture formed therein. A sensor die is coupled to an absolute support and the flex circuit. The sensor die has a diaphragm that deflects in response to air flow that flows through the air flow aperture and is incident on the diaphragm. The sensor die includes one or more gages positioned on or in the diaphragm.

Abstract: A method for establishing a wind turbine generator with one or more Permanent Magnet (PM) rotors. The method comprises the steps of: manufacturing a generator prepared for taking one or more PM rotors, manufacturing one or more rotors comprising a plurality of holding means prepared for retaining PM material, mounting substantially non-magnetized PM material prepared for magnetization in said holding means before or after said one or more rotors are mounted in said generator, connecting a magnetization system for magnetizing said PM material in the generator, and magnetizing said PM material with said magnetization system. The invention also relates to a wind turbine nacelle, a wind turbine comprising said wind turbine nacelle and use of a wind turbine.

Abstract: A method of wind tunnel measurement of airfoil, includes a step of providing a wind tunnel test apparatus. The wind tunnel test apparatus includes two walls, two supporting members, and two load measuring units. The method further includes steps of: coupling both ends of an airfoil model under test with the two supporting members, respectively; generating a flow of a fluid in the wind tunnel flow path; and measuring a load applied to the airfoil model by using the two load measuring units. A thin film member is stuck on each end of the airfoil model so that a part of the thin film member protrudes from the each end of the airfoil model along an outer circumference throughout an entire circumference. The thin film member has a strength at which the thin film member enables to endure a pressure of the fluid, and is formed of a material which is elastically deformable.

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 invention relates to a system and method for the optical calibration of the temperature of a micro-environment. The system comprises a thermochromic liquid crystal in combination with a luminophore. The steps of the method comprise providing in combination in the micro-environment at least one thermochromic liquid crystal and a luminophore, varying the temperature of the environment while irradiating the combination with light that includes light at one or more excitation wavelengths of the luminophore, and monitoring luminescence emitted by the combination while recording the temperature of the environment.

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: An aerodynamic testing apparatus includes a test object carrier that carries a test object along an orbital test path through a fluid test medium. The apparatus may be configured to carry a test object along a generally spiraling orbital test path through the fluid test medium.

Abstract: Described herein are embodiments of an apparatus for visualizing air flow around a vehicle. Such embodiments can comprise one or more gas emitters supportable by a vehicle, one or more imaging devices having a field of view of at least a portion of the gas flowing over the vehicle, and a light source for irradiating at least a portion of the field of view of the one or more imaging devices. Some embodiments of the apparatus can have a signal processor configured to generate an image based on an input from the imager. The apparatus can be configured such that the gas is not detectable to the naked eye so as to not obstruct a vehicle operator's field of vision. The apparatus can be configured to produce an image of the flow of the gas over the one or more surfaces of the vehicle when in an operational state.

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: An apparatus for pivotally fastening an aerodynamic surface. The apparatus includes a bearing block. A clamping block is connected to the bearing block and includes at least two elongate holes. A pivotally mounted strip member is coupled to the aerodynamic surface and to the clamping block. At least one fastening device is insertable into each of the at least two elongate holes for locking the clamping block relative to the bearing block. The aerodynamic surface is lockable in at least one angular position.

Abstract: A device and method for use in detecting anomalies in wind turbines is provided. The method includes monitoring data acquired by at least one sensor in a first wind turbine, wherein the data is calculated to produce a value for a predetermined amount of time, monitoring data acquired by at least one sensor in a grouping of wind turbines similar to the first wind turbine, wherein the monitored data corresponds to the monitored data of the first wind turbine and is combined for a predetermined amount of time, and comparing the monitored data of the first wind turbine with the monitored data of the grouping of wind turbines. The method also includes generating a sensor error if the monitored data of the first wind turbine deviates more than a predetermined amount from the monitored data of the grouping of wind turbines, and displaying the results of the comparison of the monitored data.

Abstract: A wind tunnel with a closed section for aeroacoustic measurements with an anechoic coating including: a) a first cavity having a thickness D1 in a range of 20?D1?50 mm filled with a fibrous material with a flow resistance R in a range of 10?R?50 kRayl/m; b) a first microperforated panel having a thickness t1 in a range of 0.25?t1?0.75 mm and with a perforation percentage p1 in a range of 15% ?p1?30%; c) a second air cavity having a thickness D2 in a range of 10?D2?30 mm; d) a second microperforated panel having a thickness t2 in a range of 0.25?t2?0.75 mm and with a perforation percentage p2 in a range of 15%?p2?30%. The perforations of the panels can be circular or longitudinal slot-shaped having a diameter d or width w in a range of 0.2?d, w?0.5 mm.

Abstract: A wind tunnel making it possible to measure the vaporization parameters of a test liquid exposed in a gas flow is disclosed. The wind tunnel comprises: a gas generator configured to generate a gas at a flow rate and at a temperature that are adjustable; a conditioning device designed to obtain a horizontal and uniform flow of the generated gas; a measurement chamber containing the liquid to be tested and various measurement devices making it possible to characterize the flow of gas passing through the measurement chamber; a tapping and analysis zone in which the gas-and-vapor mixture is tapped analyzed; and a discharge zone configured to discharge the gas-and-vapor mixture. The liquid to be tested in the tunnel presents a free surface positioned inside the measurement chamber in a manner such that it is swept continuously and tangentially by the uniform flow of gas.

Abstract: An aerodynamic testing apparatus includes a test object carrier that carries a test object along an orbital test path through a fluid test medium. The apparatus may be configured to carry a test object along a generally spiraling orbital test path through the fluid test medium.

Abstract: A system (1) for monitoring aerodynamic flow conditions over an aerodynamic member is provided. The system (1) includes a cantilevered arm (16) having a first conductive lead (18) configured for movement relative to a second conductive lead (20) for selective contact therewith in alternative response to a presence or absence of a turbulent air (22) flow thereover. In addition, the system (1) includes a circuit (24) comprising the first conductive lead (18) and the second conductive lead (20). A continuity condition in the circuit (24) between the first conductive lead (18) and the second conductive lead (20) is indicative of the presence or absence of the turbulent air flow (22).

Abstract: A system is provided for control of a structure immersed in a fluid flow regime. The system comprises a plurality of flow sensors disposed on a surface of the structure, the flow sensors including at least one flow bifurcation point sensor. The system further comprises at least one structural sensor attached to the structure for measurement of a structural parameter. A data processor in communication with the flow sensors and the at least one structural sensor is configured for processing the data signals and for generating and transmitting one or more actuator command signals to effect a desired flow and structural state for the structure. The system also comprises at least one actuator in communication with the data processor.

Abstract: A reduced scale model of a tire for aerodynamic tests in a wind tunnel, the model having a hollow toroidal shape, is made of a single molded plastic material homogeneous throughout the model, is deformable, and is shaped so as to reproduce externally the deformed shape of the tire under load when this is set in conditions of operation under the action of centrifugal loads and/or ground loads.

Abstract: The present disclosure relates to an approach by which low-performing turbines may be identified from among a plurality of wind turbines, such as may be present at a wind power plant. In accordance with one embodiment, low-performing turbines are identified from among pairs of turbines and based upon a comparison of the observed and expected performance of the turbines within each pair.

Abstract: A method of monitoring the performance of an aerodynamic surface of an aircraft. The aircraft is operated during a non-perturbed measurement period such that the flow of air over the surface is at least partially laminar. A parameter is measured which is indicative of the drag of the surface during the non-perturbed measurement period to provide non-perturbed drag data. Air flow is perturbed temporarily over the surface in a perturbed measurement period so that it undergoes a transition from laminar flow to turbulent flow. The parameter is also measured during the perturbed measurement period to provide perturbed drag data. The degree of laminar flow during the non-perturbed measurement period can then be estimated in accordance with the difference between the perturbed drag data and the non-perturbed drag data. An ice protection system can be used to perturb the air flow.

Abstract: Methods and apparatus for fast computation of fluid velocity fields in the presence of objects causing flow discontinuity are disclosed. Rigorous evaluation of perturbed velocity fields, each resulting from placing an object in a bounded space sustaining a reference velocity field, are determined for different orientations of the object with respect to a reference velocity field and different values of the magnitude of the velocity field. A velocity field is determined at selected sampling points within an enclosure surrounding the object. Pre-computed perturbed velocity fields determined for each object of a set of reference objects are stored in a computer memory. Fast real-time computation of velocity-field perturbations caused by presence of objects at arbitrary positions in a space sustaining velocity fields of different magnitudes and directions are realized using the stored pre-computed data.

Abstract: A fixture includes a housing assembly defined along an axis. A pressure bar assembly is mounted to the housing assembly for movement relative the axis. A bladder assembly is mounted at least partially within the housing assembly such that pressurization of the bladder assembly is operable to exert a force on a workpiece along the axis with the pressure bar assembly.

Abstract: A test section for a wind-tunnel testing apparatus has a mounting section that mounts an automobile along the internal floor surface of a wind tunnel. Tests are conducted by applying an airflow blown in the wind tunnel to the automobile mounted on the mounting section. The test 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 method for determining the speed of at least one rotating fan, such as a propeller, through sensing pressure waves generated by the blades of the fan. An apparatus operable to execute the method is also disclosed. The apparatus includes a fan having a hub portion and a plurality of blades extending radially outward from the hub portion. The apparatus also includes an engine operable to rotate the fan about an axis of rotation. The apparatus also includes a sensor spaced from the fan along the axis of rotation. The sensor is positioned to sense at least one physical condition that is external of the engine and is changed by rotation of the plurality of blades. The sensor is operable to emit a signal corresponding to at least one physical condition. The apparatus also includes a processor operably engaged with the engine and the sensor. The processor is operable to receive the signal from the sensor and change the operation of the engine in response to the signal to change a speed of the fan.

Abstract: A load measuring system for measuring the loads on a foundation for wind turbines is disclosed. A load measuring device is mounted on a rock anchor pad for a turbine and measures the loads on the anchor. Signals from the load measuring device are transmitted to a remote location. The load measuring device is installed on selected rock anchor pads, distributed evenly about the foundation pad. The signals from the load measuring are transmitted to a control station at a remote location, thereby enabling continuous monitoring of the loading conditions on the rock anchors. The signals from a plurality of load measuring systems may be transmitted to the control station, so as to allow monitoring of a group of wind turbine foundation pads at a single location.

Abstract: A monitoring system for monitoring a test article includes a scanning system and a computer system. The test article may be positioned within a fluid tunnel. The scanning system may be configured to scan the test article and record positional data of at least one point on an article surface of the test article. The computer system is in communication with the scanning system for receiving the positional data and being operative to determine at least one of the following: a position of the test article, an attitude of the test article, and deformation of the article surface.

Abstract: A bicycle fitting system includes a wind tunnel, a platform, a load cell, a bicycle rig, a plurality of actuators, and a processor. The platform is disposed within the wind tunnel and includes a rear roller, a front strut, and a rear strut. The load cell is coupled to the platform. The bicycle rig is coupled to the front and rear struts and includes a plurality of adjustment points, a rear wheel, a handle bar, and a seat, with the rear wheel friction coupled to the rear roller. Each adjustment point is associated with one of the actuators, and each actuator is operable to alter a configuration of the bicycle rig. The processor receives an output from the load cell and operates the actuators while a rider is riding the bicycle rig.

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 computer-aided method suitable for assisting in the design of an aircraft by providing the dimensioning aerodynamic forces and other relevant values comprising the following steps: a) Selecting a set of parameters of the aircraft, being said aerodynamic forces and other relevant values dependant of said parameters; b) Performing flow field CFD RANS computations for a number N1 of different combination of values of said parameters; c) Obtaining said aerodynamic forces and other relevant values for whatever combination of values of said parameters through a reduced-order model, generated by computing the POD modes of the flow variables, expanding the flow variables using said POD modes and obtaining the POD coefficients of said expanded flow variables using a genetic algorithm that minimizes the error associated to the expansion of the Navier-Stokes equations. The invention also refers to a system for carrying out said method.

Abstract: A system for simultaneously creating severe acoustic, thermal and airflow environmental conditions is described. The system includes a jig for mounting a test article, a jet engine, and a nozzle attached to the jet engine. The nozzle includes an opening for defining a two dimensional exhaust flow from the jet engine to create an acoustical, thermal and airflow environment across the test article. The jig is operable for maintaining a position of the test article with respect to the nozzle.

Abstract: In-flight testing methods and kits for in-flight testing of proposed aerodynamic structures are disclosed. The methods and kits involve a testing station carried on a pre-existing fully engineered and tested host aircraft. Interchangeable but differently configured aerodynamic structures may be carried upon the host aircraft, and existing systems of the host aircraft may be utilized to conduct the testing, avoiding time and cost associated with constructing fully operational demonstrator aircraft for testing purposes.

Abstract: A piezoresistive sensor assembly is provided that has a flex circuit having at least one air flow aperture formed therein. A sensor die is coupled to an absolute support and the flex circuit. The sensor die has a diaphragm that deflects in response to air flow that flows through the air flow aperture and is incident on the diaphragm. The sensor die includes one or more gages positioned on or in the diaphragm.

Abstract: A method of wind tunnel measurement of airfoil, includes a step of providing a wind tunnel test apparatus. The wind tunnel test apparatus includes two walls, two supporting members, and two load measuring units. The method further includes steps of: coupling both ends of an airfoil model under test with the two supporting members, respectively; generating a flow of a fluid in the wind tunnel flow path; and measuring a load applied to the airfoil model by using the two load measuring units. A thin film member is stuck on each end of the airfoil model so that a part of the thin film member protrudes from the each end of the airfoil model along an outer circumference throughout an entire circumference. The thin film member has a strength at which the thin film member enables to endure a pressure of the fluid, and is formed of a material which is elastically deformable.

Abstract: The present invention relates to microelectromechanical systems (MEMS). In particular, the present invention relates to MEMS arrays for use in acoustics and other applications.

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 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: The present invention is a vertical wind tunnel amusement device. The device comprises a flight chamber wherein a user may experience a freefall through the atmosphere from the safety of an enclosed flight chamber. Airflow sufficient to fully support a user within the flight chamber is induced by a plurality of fans connected above the flight chamber through a duct. A staging area having openings to the flight chamber is adjacent to the flight chamber. A user may enter or retreat from the flight chamber at will through the staging area openings without significantly adjusting the airflow velocity in the flight chamber. A control room is adjacent to the fight chamber whereby an operator may observe a user or users within the flight chamber and thereby safely control the operation of the fans. A projection room is also adjacent to the flight chamber whereby a video of a skydiving experience may be displayed to a user within the flight chamber.