Loads were measured at altitudes to 35,000 ft and Mach numbers to 0.82; data from rudder step, aileron-roll, and steady sideslip maneuvers were reduced to give derivatives of horizontal tail normal force and rolling moment coefficients with respect to sideslip angle and rate of change of wing fuselage combination pitching moment coefficient with sideslip angle.
Analysis of incremental horizontal-tail loads measured on swept-wing bomber airplane in sideslip maneuvers
NASA -- Tech Note
1959
34 pages
Report
English
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Analysis of horizontal-tail loads in pitching maneuvers on flexible swept-wing jet bomber
Engineering Index Backfile | 1957
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