Estimates of the static stick-fixed stability and control characteristics of the Consolidated Vultee model 240 airplane are presented in this report. The estimates are based on tests of a 0.092-scale powered model in the 10-foot wind tunnel of the Guggenheim Aeronautical Laboratory of the California Institute of Technology. Results of the analysis are evaluated in terms of the Army specifications for stability and control characteristics which are more specific and, in general, equal to or more rigid than the Civil Aeronautics Administration requirements. The stick-fixed stability and control characteristics of the Consolidated Vultee model 240 were found to be satisfactory except for the following: 1) Marginal longitudinal stability in the landing approach (flaps 30 deg, 50 minimum continuous power) with aft center of gravity (31 M.A.C.); 2) Marginal rudder control to hold zero sideslip in a climb after take-off with asymmetric power (flaps 30 deg, left engine inoperative, right engine delivering take-off power) with maximum rudder throw limited to /- 18 deg; 3) Marginal dihedral effect with flaps 40 deg and engines delivering maximum continuous power.
Stock-Fixed Stability and Control Characteristics of the Consolidated Vultee Model 240 Airplane as Estimated From Tests of A 0.092-Scale Powered Model
1947
28 pages
Report
No indication
English
Aerodynamics , Aircraft , Wind tunnel tests , Static stability , Aircraft control , Sideslip , Climbing flight , Later stability , Longitudinal stability , Aircraft stability , Aircraft models , Powered models , Flaps (Control surfaces) , Center of gravity , Aircraft landing , Approach , Aerial rudders
Engineering development work of consolidated vultee aircraft corporation
Engineering Index Backfile | 1943
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