Development of a Data Acquisition System to Aid in the Aerodynamic Study of Various Helicopter Configurations.
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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This thesis developed a data acquisition system to be used in conjunction with the 3.5 x 5.0 low speed wind tunnel at the Naval Postgraduate School. Interactive graphic programs were developed to aid in data acquisition and analysis. In addition, the internal balance that was designed by Major Scott Mair and Major Chris Sargent was redesigned to correct some problems encountered with the drag component. The balance was also instrumented to record the pitch and yaw moment components. A calibration rig was designed and constructed in order to evaluate the interactions to the different components. The equipment used and computer programs developed for data acquisition and analysis were adequate. However, balance calibration revealed problems with the calibration rig and location of the roll component strain gage. Both of these problems will have to be corrected before accurate readings can be expected from this balance design. Keywords Data recuction Landing gear design Helicopter noses and tails. Author
- Computer Programming and Software
- Test Facilities, Equipment and Methods
- Human Factors Engineering and Man Machine Systems