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Stick-Fixed Stability and Control Characteristics of the Consolidated Vultee Model 240 Airplane as Estimated from Tests of a 0.092-Scale Powered ModelEstimates 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.
Document ID
20030063966
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
McCullough, George B. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Weiberg, James A. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Gault, Donald E. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
June 27, 1947
Subject Category
Aircraft Stability And Control
Report/Patent Number
NACA-RM-A7F19
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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