Effects of sideslip angle, rudder deflection, and Mach number are presented for trim flight at altitudes from 40,000 to 70,000 ft and at Mach numbers from 0.70 to 2.08; comparisons made with simple theoretical methods of estimating loads; total directional stability for each aircraft as calculated by use of vertical tail loads is shown.
Vertical-tail loads measured in flight on four airplane configurations at transonic and supersonic speeds
NASA -- Tech Note
1960
31 pages
Report
Englisch
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