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Pressure-sensitive paint (PSP) is a method for measuring air pressure or local oxygen concentration, usually in aerodynamic settings. PSP is paint-like coating which fluoresces under a specific illumination wavelength in differing intensities depending on the external air pressure being applied locally to its surface.
A model surface is painted with the PSP coating with an airbrush or automotive type paint gun. The PSP consists of an oxygen sensitive probe suspended in an oxygen permeable binder. The model is then placed in an oven so the PSP layer can cure. Once cured, the model is placed in a wind tunnel or appropriate test environment. LED lamps of a specific wavelength are used to excite the pressure-sensitive probe within the paint. Once excited, the pressure-sensitive probe is transitioned to a higher energy state where it may either emit a photon or be quenched by local oxygen present. This competing process of emission and quenching determines the intensity response of the paint layer. The result is a dimmer fluorescence where there is higher pressure and brighter response at lower pressures.
The intensity emitted from the surface is then recorded through a long-pass filter by a CCD or scientific grade camera and stored for conversion to pressure using a previously determined calibration. Images of the paint layer are recorded at three conditions. A wind-off image at a known reference condition which is typically standard atmospheric conditions with the tunnel turned off. A wind-on image at a loaded condition where the wind tunnel is running at condition. And lastly a background image where the ambient light present is captured without the illumination source. The background image is then subtracted from the wind-off reference and the wind-on condition image in data processing. Photographs of the surface can be obtained from outside the wind tunnel's test section, which means that the model need never be disturbed or touched in order to obtain the pressure distribution. Computer-aided photography can be used to produce false-color images, where the color range corresponds to the pressure variations. [1]
Due to the high cost of constructing airplanes, the first designs of proposed aircraft are usually subjected to aerodynamic testing in wind tunnels. In these tunnels, models (usually subscale) are subjected to airflows to simulate an actual airplane in free flight. The aerodynamic forces acting on the model are measured, and are used to predict the response of an airplane when subjected to equivalent airflows.
Automobiles are also subjected to aerodynamic testing in wind tunnels. Automobile companies use data collected in these tests to measure areas of high and low pressure. This data helps engineers improve designs to increase performance for the vehicles. By changing these designs, engineers can help improve gas mileage and reduce noise. [2]
In order to measure the aerodynamic forces on the whole model, beam balances are connected to the model. However, it is also imperative to understand how those forces are distributed across the aerodynamic surfaces of the aircraft, and this understanding is more difficult to obtain. The classic approach has been to use an array of pressure taps to measure surface pressure distributions on a model. Pressure taps provide limited spatial resolution and are often limited by model geometry and can be very expensive to integrate into complex geometries.
PSP provides a low-cost alternative that is less invasive than pressure tap arrays. PSP also offers superior spatial resolution, with each pixel of the imaging camera acting as a pressure tap. PSP can achieve accuracy within 150 Pa of pressure tap measurements with good setup and experience.
Time-resolved PSP applications involve pulsed excitation and delay and gating of the imaging devices. One can thus determine pressure differentials as a function of time. In this case, the imaging devices must be synchronized to the excitation. Multi-channel digital delay/pulse generators provide that synchronization.
Another area of interest has been the measurement of surface pressure in low-speed wind tunnels. Binary PSP systems are used in low-speed wind tunnel environments where pressure gradients are small and error sources are more significant. Model shift between reference condition and loaded condition, variation in paint thickness, lamp instability, and temperature are significant sources of error in PSP data. Binary PSP mitigates many of these error sources by employing a second probe into the paint layer, known as the reference probe. This reference probe is used to ratio out the effects of these errors producing high quality PSP pressure maps at low speeds.
The greatest advantage of the new technology is its much reduced preparation time compared to installing an array of pressure taps. The same model can be used for other testing, such as load-bearing tests or radar-reflection tests, since the PSP will not interfere with other preparations or setups. There are far more data points than other methods. There is essentially a "pressure tap" at every pixel instead of being limited to the actual pressure taps.
Aerodynamics, from Greek ἀήρ aero (air) + δυναμική (dynamics), is the study of the motion of air, particularly when affected by a solid object, such as an airplane wing. It involves topics covered in the field of fluid dynamics and its subfield of gas dynamics.The term aerodynamics is often used synonymously with gas dynamics, the difference being that "gas dynamics" applies to the study of the motion of all gases, and is not limited to air. The formal study of aerodynamics began in the modern sense in the eighteenth century, although observations of fundamental concepts such as aerodynamic drag were recorded much earlier. Most of the early efforts in aerodynamics were directed toward achieving heavier-than-air flight, which was first demonstrated by Otto Lilienthal in 1891. Since then, the use of aerodynamics through mathematical analysis, empirical approximations, wind tunnel experimentation, and computer simulations has formed a rational basis for the development of heavier-than-air flight and a number of other technologies. Recent work in aerodynamics has focused on issues related to compressible flow, turbulence, and boundary layers and has become increasingly computational in nature.
Wind tunnels are large tubes with air blowing through them which are used to replicate the interaction between air and an object flying through the air or moving along the ground. Researchers use wind tunnels to learn more about how an aircraft will fly. NASA uses wind tunnels to test scale models of aircraft and spacecraft. Some wind tunnels are large enough to contain full-size versions of vehicles. The wind tunnel moves air around an object, making it seem as if the object is flying.
Atmospheric entry is the movement of an object from outer space into and through the gases of an atmosphere of a planet, dwarf planet, or natural satellite. There are two main types of atmospheric entry: uncontrolled entry, such as the entry of astronomical objects, space debris, or bolides; and controlled entry of a spacecraft capable of being navigated or following a predetermined course. Technologies and procedures allowing the controlled atmospheric entry, descent, and landing of spacecraft are collectively termed as EDL.
In fluid dynamics, a stall is a reduction in the lift coefficient generated by a foil as angle of attack increases. This occurs when the critical angle of attack of the foil is exceeded. The critical angle of attack is typically about 15°, but it may vary significantly depending on the fluid, foil, and Reynolds number.
Automotive aerodynamics is the study of the aerodynamics of road vehicles. Its main goals are reducing drag and wind noise, minimizing noise emission, and preventing undesired lift forces and other causes of aerodynamic instability at high speeds. Air is also considered a fluid in this case. For some classes of racing vehicles, it may also be important to produce downforce to improve traction and thus cornering abilities.
Atomic force microscopy (AFM) or scanning force microscopy (SFM) is a very-high-resolution type of scanning probe microscopy (SPM), with demonstrated resolution on the order of fractions of a nanometer, more than 1000 times better than the optical diffraction limit.
A DNA microarray is a collection of microscopic DNA spots attached to a solid surface. Scientists use DNA microarrays to measure the expression levels of large numbers of genes simultaneously or to genotype multiple regions of a genome. Each DNA spot contains picomoles of a specific DNA sequence, known as probes. These can be a short section of a gene or other DNA element that are used to hybridize a cDNA or cRNA sample under high-stringency conditions. Probe-target hybridization is usually detected and quantified by detection of fluorophore-, silver-, or chemiluminescence-labeled targets to determine relative abundance of nucleic acid sequences in the target. The original nucleic acid arrays were macro arrays approximately 9 cm × 12 cm and the first computerized image based analysis was published in 1981. It was invented by Patrick O. Brown. An example of its application is in SNPs arrays for polymorphisms in cardiovascular diseases, cancer, pathogens and GWAS analysis. It is also used for the identification of structural variations and the measurement of gene expression.
An airfoil or aerofoil is the cross-sectional shape of an object whose motion through a gas is capable of generating significant lift, such as a wing, a sail, or the blades of propeller, rotor, or turbine.
JTAG is an industry standard for verifying designs and testing printed circuit boards after manufacture.
A leading-edge cuff is a fixed aerodynamic wing device employed on fixed-wing aircraft to improve the stall and spin characteristics. Cuffs may be either factory-designed or an after-market add-on modification.
A Trisonic Wind Tunnel (TWT) is a wind tunnel so named because it is capable of testing in three speed regimes – subsonic, transonic, and supersonic. The earliest known trisonic wind tunnel was dated to 1950 and was located in El Segundo, California before it closed in 2007. Other trisonic wind tunnels currently in operation are those located at NASA's Marshall Space Flight Center and the French-German Research Institute of Saint-Louis.
In aeronautics, expansion and shock tunnels are aerodynamic testing facilities with a specific interest in high speeds and high temperature testing. Shock tunnels use steady flow nozzle expansion whereas expansion tunnels use unsteady expansion with higher enthalpy, or thermal energy. In both cases the gases are compressed and heated until the gases are released, expanding rapidly down the expansion chamber. The tunnels reach speeds from Mach 3 to Mach 30 to create testing conditions that simulate hypersonic to re-entry flight. These tunnels are used by military and government agencies to test hypersonic vehicles that undergo a variety of natural phenomenon that occur during hypersonic flight.
The Kline–Fogleman airfoil or KF airfoil is a simple airfoil design with single or multiple steps along the length of the wing. It was originally devised in the 1960s for paper airplanes.
Cyclone Business Jet (CBJ) is an undergraduate student organization at Iowa State University, undertaking the task of designing and constructing a prototype 10-passenger commuter or business class jet airplane. It is composed mostly of Aerospace Engineer majors, however there are also Mechanical and Civil Engineers as well as Design majors. Emphasis is taken in designing for lower cost and greater fuel range. Teams are broken off into three sub-groups: the Aerodynamics Team, Performance Team, and Structures Team. The goal of Cyclone Business Jet is to apply classroom acquired skills to a real life problem with a finished product in mind.
Flow conditioning ensures that the “real world” environment closely resembles the “laboratory” environment for proper performance of inferential flowmeters like orifice, turbine, coriolis, ultrasonic etc.
Standard wind tunnel models, also known as reference models, calibration models or test check-standards are objects of relatively simple and precisely defined shapes, having known aerodynamic characteristics, that are tested in wind tunnels. Standard models are used in order to verify, by comparison of wind tunnel test results with previously published results, the complete measurement chain in a wind tunnel, including wind tunnel structure, quality of the airstream, model positioning, transducers and force balances, data acquisition system and data reduction software.
AGARD-B is a standard wind tunnel model that is used to verify, by comparison of test results with previously published data, the measurement chain in a wind tunnel. Together with its derivative AGARD-C it belongs to a family of AGARD standard wind tunnel models. Its origin dates to the year 1952, and the Second Meeting of the AGARD Wind Tunnel and Model Testing Panel in Rome, Italy, when it was decided to define two standard wind tunnel model configurations to be used for exchange of test data and comparison of test results of same models tested in different wind tunnels. The idea was to establish standards of comparison between wind tunnels and improve the validity of wind tunnel tests. Among the standard wind tunnel models, AGARD model configuration B (AGARD-B) has become by far the most popular. Initially intended for the supersonic wind tunnels, the AGARD-B configuration has since been tested in many wind tunnels at a wide range of Mach numbers, from low subsonic, through transonic to hypersonic. Therefore, a considerable database of test results is available.
The operation of a photon scanning tunneling microscope (PSTM) is analogous to the operation of an electron scanning tunneling microscope, with the primary distinction being that PSTM involves tunneling of photons instead of electrons from the sample surface to the probe tip. A beam of light is focused on a prism at an angle greater than the critical angle of the refractive medium in order to induce total internal reflection within the prism. Although the beam of light is not propagated through the surface of the refractive prism under total internal reflection, an evanescent field of light is still present at the surface.
The MARHy Hypersonic low density Wind Tunnel, located at the ICARE Laboratory in Orléans, France, is a research facility used extensively for fundamental and applied research of fluid dynamic phenomena in rarefied compressible flows. Its name is an acronym for Mach Adaptable Rarefied Hypersonic and the wind tunnel is recorded under this name under the European portal MERIL.
The PHEDRA High Enthalpy low density Wind Tunnel, located at the ICARE Laboratory in Orléans, France, is a research facility used extensively for fundamental and applied research on non equilibrium plasma flows and planetary atmospheric entries. Its name is an acronym for soufflerie à Plasma Hors Equilibre de Rentreés Atmosphériques. Phedra wind tunnel takes part of the European Landscape Network portal MERIL.
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