On the prediction of auto-rotational characteristics of light airplane fuselagesA semi-empirical theory is presented for the estimation of aerodynamic forces and moments acting on a steadily rotating (spinning) airplane fuselage, with a particular emphasis on the prediction of its auto-rotational behavior. This approach is based on an extension of the available analytical methods for high angle of attack and side-slip and then coupling this procedure with strip theory for application to a rotating airplane fuselage. The analysis is applied to the fuselage of a light general aviation airplane and the results are shown to be in fair agreement with experimental data.
Document ID
19840059570
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pamadi, B. N. (Indian Institute of Technology Bombay, India)
Taylor, L. W., Jr. (NASA Langley Research Center Hampton, VA, United States)