Upgrade of a LabVIEW Based Data Acquisition System for Wind Tunnel Test of a 1/10 Scale OH-6A Helicopter Fuselage
| Author | : | |
| Rating | : | 4.70 (947 Votes) |
| Asin | : | 1423501136 |
| Format Type | : | paperback |
| Number of Pages | : | 99 Pages |
| Publish Date | : | 0000-00-00 |
| Language | : | English |
DESCRIPTION:
Thesis abstract takes credit that is false The author makes claims that are not true.1. New data acquisition hardware was installed three years ago but never fully verified: Not independently verified by an outside agency, but I verified it with the help of NASA AMES Engineers and so did my thesis advis
wind tunnel, along with the U.S. NPS Aerolab wind tunnel tests consisted of drag, lift, and pitching moment measurements of the OH-6A along yaw and angle-of attack sweeps. It has been reproduced in the best form available to the Pentagon. The results of the NPS wind tunnel data were compared against testing conducted on a full-scale OH-6A helicopter in NASA Ames' 40 ft. The Virtual Instruments (VI) program collects and plots accurate data from all four strain gauges in real-time, producing non-dimensional force and moment coefficients. This is a NAVAL POSTGRADUATE SCHOOL MONTEREY CA report procured by the Pentagon and made available for public release. A research study on the performance of an OH-6A helicopter fuselage was conducted. x 80ft. New data acquisition hardware was installed three years ago but never fully verified, and contained no integrated software program to collect data from the strain-gauge balance pedestal. It is not spiral-bound, but rather assembled with Velobinding in a soft, white linen cover. The Storming Media report number is A575714. Existing National Instruments based hardware for the NPS low-speed wind tunnel was reconfigured to obtain data from the strain- gauge pedestal. Additionally, a data acquisiti