Wind Tunnel Drag Evaluations of Helicopter Nose Sections.
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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This thesis determines the aerodynamic drag parameters for three different generic helicopter nose fuselage sections at various angles of attack and velocities using a 3.5 x 5 foot wind tunnel and a locally constructed three component strain gage balance. A common center section is used with provisions for three different tail sections allowing for nine possible configurations to effect the overall shape of a fuselage. This allows a student in a basic conceptual helicopter design course a quantitative means of comparing general shapes in order to select the best configuration of the fuselage. However, the results are questionable due to problems with the strain gage balance used to determine the aerodynamic forces on the models. Keywords Minitufts Helicopter nose sections Strain gage balance interaction.
- Test Facilities, Equipment and Methods