Publication Date:
2019-07-13
Description:
The dynamic equations of motion for a spinning airplane are simplified to facilitate the analysis of spin entry and recovery maneuvers. Solutions of a nonlinear, first order equation for spin rate enable calculation of spin entry and recovery times and control required for recovery. The analysis is applied to a light airplane for which both aerodynamic data, rotory balance wind tunnel tests, and spin flight test data have been obtained. A comparison of predicted and actual transient spin responses is made which supports the validity of the analytical approach taken but which also illustrates the difficulty in obtaining accurate aerodynamic data for spinning airplanes. Certain normalized parameters of the reduced state spin equation suggest criteria for assessing the transient spin characteristics of light airplanes.
Keywords:
AIRCRAFT STABILITY AND CONTROL
Type:
AIAA PAPER 82-0243
,
Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
Format:
text
