A propeller design and analysis capability evaluation for high altitude application
Date
2011-04-15
Authors
Monk, John Steven
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Abstract
The purpose of this research is the evaluation of a relatively simple minimum induced loss
propeller design and a radially-graded momentum theory analysis method to provide the initial
propeller design and analysis capability for predicting propeller performance of a High Altitude
Long Endurance (HALE) flight vehicle. These design and analysis capabilities cover flight
conditions from take off at sea level to the low air density, high true airspeeds and high blade
Mach numbers of high altitude flight. A conceptual propeller was designed and its
performance analysed within a time-stepped mission simulation code. Wind tunnel tests were
carried out on a scaled model of the propeller comparing actual performance against
theoretical predictions. The design method was shown to be capable of producing a propeller
design that could provide sufficient thrust over a large range of advance ratios (0.12 to 0.4)
and altitudes (0 to 15 000 m). Agreement between the predicted and measured results is
particularly good at the lower thrust coefficients and advance ratios, at higher power
coefficients and advance ratios increasing differences between the predicted and measured
results became apparent.