Experimental methods for the investigation of trailing vortex strengths, total lift, and lift distributions for three-dimensional wings in close proximity flight were developed. With these experiments we model compound aircraft flight either docked tip-to-tip, or flying in formation. There is a distinct lack of experimental formation flight data using three-dimensional wing models for tests. The absence of fixed walls on either end of the wing permits the development of the asymmetric shedding of vortices, and the determination of the asymmetric circulation distribution induced by the proximity of the leading wing. The pair consisted of a swept NACA-0012 non-cambered wing simulating one half of a leading aircraft and a rectangular cambered NACA 63-420 wing simulating the trailing aircraft. Important aspects of the work included theoretical development, experimental setup, data acquisition and processing, and results validation.Experimentally determining the lift for formation flight, in addition to the local flow behavior for a pair of wings, can provide valuable insight for the proposition of flying actual aircraft in formation to increase mission efficiency. To eliminate the need for bulky mounting stings and direct load measurement devices that can potentially interfere with the local flowfield, a minimally invasive velocity probe method is developed. A series of experiments were performed to assist with the development of the method. Velocity and vorticity distributions obtained along a near-field plane were processed to calculate wingtip vortex strengths. Additionally, vortex position instabilities and the shedding of vorticity inboard of the wingtips were observed. To determine the circulation distributions for the trailing wing, the initial method is modified. By processing velocity information acquired in a near-field plane, both the lift and induced drag were calculated for the trailing airfoil. Comparisons are made to directly measured loads and to results reported earlier. Directly measured lift and drag coefficients were found to agree with existing literature.iii DedicationCreation seems to come from imperfection. Creation of a significant entity when beginning with something imperfect is the ability to achieve. To every person who cannot, will not, and then does not give up nor give in when trying to accomplish what seems to be the impossible. You will prevail.iv Acknowledgements I would like to thank my primary advisor, Dr. Demetri Telionis, first and foremost for providing me with guidance as needed throughout the duration of my studies. He has always been available whenever I was in need of assistance. I would also like to extend appreciation to Dr. Pavlos Vlachos, and Dr. Saad Ragab for serving on my graduate advisory committee. Although I didn't often seek out their expertise, of which they both have much in their respective fields, I have no doubt that they would have welcomed my inquiries without hesitation.In addition to my technical advisors, I would like to express gratitude towards my pa...

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Based on technologies developed for the Jet Propulsion Laboratory (JPL) Free-Hying-Magnetometer (PPM) concept,' we propose to modify the present design of FFMs for detection of mines and arsenals with large magnetic signature. The result will be an integrated miniature sensor system capable of identifying local magnetic field anomaly caused by a magnetic dipole moment. Proposed integrated sensor system is in line with the JPL technology road-map for development of autonomous, intelligent, networked, integrated systems with a broad range of applications. In addition, advanced sensitive magnetic sensors (e.g; silicon micromachined magnetometer, laser pumped helium magnetometer) are being developed for future NASA space plasma probes.It is envisioned that a fleet of these Integrated Sensor Systems (ISS) units will be dispersed on a mine-field via an aerial vehicle (a low-flying airplane or a helicopter). The number of such sensor systems in each fleet and the corresponding in-situ probe-grid cell size is based on the slrength of magnetic anomaly of the target and 155 measurement resolution of magnetic field vector. After a specified time, 155 units will transmit the measured magnetic field and attitude data to an air-borne platform for further data processing. The cycle of data acquistion and transmission will be continued until batteries run out. Data analysis will allow a local deformation of the Earth's magnetic field vector by a magnetic dipole moment to be detected.Each 155 unit consists of miniaturized sensitive 3-axis magnetometer, high resolution analog-to-digital converter (ADC), Field Programmable Gate Array (FPGA)-based data subsystem, Li-batteries and power regulation circuitry, memory, S-band transmitter, single-patch antenna, and a sun angle sensor. 155 unit is packaged with non-magnetic components and the electronic design implements low-magnetic signature circuits. Care is undertaken to guarantee no corruption of magnetometer sensitivity as a result of its close proximity with the electronics and packaging materials. Accurate calibration of the magnetometer response in advance will allow removing the effects of unwanted disturbances. Improvements of the magnetometer performance in the areas of the orthogonality, drift, and temperature coefficient of offset and scale factor are requirecL