 This video supplement is composed of eight sequences, each of which is referenced in the report. These dynamic demonstrations, primarily of F106B flight vapor screen images, obtained using a rotating light sheet, have been designed to provide insight into the process of developing quantifiable results from this data. For a complete description of the image data, its analysis, and the analyses of other types of data as well, the formal document should be consulted. This flight experiment was done in order to examine vertical flow field characteristics on a highly swept wing at full-scale flight conditions. An F106B fighter interceptor airplane was chosen because of its wide flight envelope, allowing data to be gathered over a range of angles of attack and Mach numbers, as well as Reynolds numbers. The test aircraft was outfitted with flow visualization equipment adapted from wind tunnel experimentation. A rotating thin sheet of light was produced by a mercury arc lamp with a slidden lens arrangement. This illumination permitted the general characteristics of the vortex, made visible by a trained seated vapor, to be recorded by two video cameras focused over the wing's upper surface. Flight planning to obtain desired flight conditions resulted in two types of maneuvers, one G flight at various speeds and altitudes, and descending spiral turns. Meteorological conditions were a chief limiting constraint. Test instrumentation on board the aircraft was restricted from flight through clouds or precipitation. Flights could only be made at night during periods of no-moon elimination to ensure sufficient contrast for the video cameras. The light sheet and vapor generator were controlled by an engineer in the aft cockpit. A video display showed the image from either camera along with angle of attack and light sheet position. Flight data were recorded on board and telemetered to a ground station at NASA Langley. The primary data collected was video. At night, the wing was not visible and only the light sheet and vapor cross section over the wing could be seen. On point data collection proceeded with a light sheet sweep across the wing, as well as several discreet light sheet locations for post-flight analysis. Additional flights were made during daylight with an oil mixture painted on the wing to show surface flow patterns. An integrated computer process combining image processing, computer graphics, and photogrammetric reconstruction techniques was utilized to aid in three-dimensional visualization of images produced by the rotating light sheet. Accurate surface definition of the aircraft was simulated through original engineering drawings, including geometric description of wings, fuselage, and vertical tail, all of which were collectively rendered to produce a smooth three-dimensional model. An additional input into this environment was a set of parameters describing the placement of the two cameras on board the F106B. Several targets were placed upon the wing upper surface and their coordinates measured to facilitate the calibration of the cameras. The raw video footage captured by the cameras in flight provided only qualitative information as to the size and placement of vortices above the wing. Each image had a perspective distortion produced as the light sheet rotates away from the stationary cameras. To account for these irregularities and extract quantitative geometric information from the images, a photogrammetric reconstruction technique was developed. This technique mapped each point in the image plane of a camera to a precise location in the plane of the light sheet. Camera orientation and imaging properties as well as light sheet position and angle were measured to provide accurate calculations. Once a set of data for a specified test condition was constructed, the 3D coordinate of any point in the flow field could be determined. Vortex core paths determined from image centroids as well as the approximate reattachment lines could be extracted and displayed simultaneously. The same sequence of operations was applied to the side camera image such that both camera data sets were combined into one interactive display. Selected frames from videotapes for each flight were digitized on the data visualization and animation lab's video image processing system. The video image processing system is a combination of hardware and software designed to provide interactive capability for processing videotape images of wind tunnel or in-flight experiments. The system, controlled from a host computer, consists of an image processing system, video equipment, and a real-time digital disc. The software interface is a commercially available image processing software system. The system is designed to accept common video formats including the SVHS and VHS formats used in this flight test. This software allows VCR control from the computer station. Video footage is digitized and stored to digital disc at 30 frames per second. Once rendered to real-time disc, the images are slowed down during playback and examined in slow motion. Timecode information appearing in the lower left corner uniquely identifies each image. Selected images were stored on a disc for post-processing. With the use of extractor software, the core locations for a vortex system were determined by examining each pertinent image. The show movie of this directory option enables an overall impression of flow over the wing at the test condition and allows the determination of how many vortices are present and the progression. Beginning with the first image to be examined, invoke the define region of interest for this image option and use the mouse to circumscribe the region where the core is thought to be located. The horizontal and vertical pixel values for this core are saved. However, if other cores are present on this image, they must also be determined and saved before proceeding. The same steps are repeated for other images. After all the images for the dataset have been processed, the wave program is exited and the core pixel values, up to four sets per image, are moved to a permanent file. To determine the reattachment points, the extractor software is once again used. The outer part of the vortex is projected vertically to the forward part of the light sheet footprint. This is followed by a circumscription of a small region on the footprint with the mouse. After the horizontal and vertical pixel values for the pointer found, they are saved. When other reattachment points are present on this image, they must also be determined and saved before proceeding. Prior to saving all these pixel values, consistency in the criterion used to determine reattachment points is checked. These steps are repeated for the other images. After all the images for the dataset have been processed, the wave program is exited and the reattachment point pixel values, up to four sets per image, are moved to a permanent file. To display vortex flow features is characterized by the vapor screen image in core location with reattachment points in a three-dimensional mode. A silicon graphics iris workstation and the flow analysis software toolkit called FAST was utilized. Once logged on to the iris, a remote login is done to a host computer containing the image files along with core location and reattachment point files. With a FAST script written for this purpose, it is simple to obtain the vortex system features on a wing by keying in the corresponding points. This generates the feature from both the top and side cameras in terms of the three-dimensional coordinates consistent with the aircraft and then displays them on the surface geometry. By using the capabilities of FAST, the resulting three-dimensional representation can be moved until it resembles the NASA technical paper. In 1985, a stationary light sheet was used to illuminate a fixed cross-section of the flow field above the wing of the F106B. A camera calibration was not performed at the time of this flight. Thus, the photogrammetric reconstruction technique could not be applied. Spatial information was obtained before the flights by placing a physical grid of regularly spaced six-inch squares in the plane of the light sheet. When the grid was photographed by the camera in its flight position, a prospective distortion was introduced. The distortion was corrected using a warping procedure to produce an image in which the grid lines were regularly spaced. The warping technique was applied to selected vapor screen images from 1985 and the resulting images were evenly distributed across the light sheet plane to reconstruct approximate 3D coordinates. When loaded into the FAST program, the vapor screen images produced by the stationary light sheet in 1985 could be correlated with those obtained from the rotating light sheet in 1991. The vortex core paths and reattachment lines extracted from the 1991 flight data could be displayed simultaneously. With the enhancer software, the vortex system details can be enhanced. The code expects the user to key in the starting and ending light sheet angles, as well as the file name containing the group of files to consider. The code displays all the images in the group and asked whether or not a particular image is to be included for enhancement. Choosing the Enhance This Image option for the first image leads to yet another menu. A 3x3 smoothing on each image is imposed a total of three times in combination with the Continue Enhancement to the Image Process option. The Contrast Stretch option is used to spread the entire range of pseudo colors in such a way as to emphasize the existing gradation in this image. The Contour option allows selected colors to be set to black, thereby forming contours. Finally, the Save Enhanced Flight Image option is used, which displays the image with an identification code and then saves it. The photogrammetric reconstruction technique, which maps vapor images onto light sheet planes, was extended to project imagery onto any arbitrary surface composed of polygons. This extension was specifically used to project oil flow patterns videotaped by the top camera onto the polygonal model of the wing surface. Vapor screen images, core paths, and reattachment lines extracted from the rotating light sheet could then be displayed simultaneously for a direct comparison. This video supplement has been designed to demonstrate the computer graphics capabilities utilized in developing data which are presented in the report. The viewer is reminded that this supplement does not report to present the complete set of various data types or the attended analyses, both of which are contained in the NASA technical paper. Therefore, the viewer is referred to the formal report for the complete documentation of this work.