Test results indicated that, if airplane were not stalled, total up load of 5700 lb would be experienced on horizontal tail in 8g pull-up and that, with power on, this load would be distributed unsymmetrically with about 800 lb more up load on left stabilizer than on right. (published 1948) (15¢)
Flight studies of horizontal-tail loads experienced by fighter airplane in abrupt maneuvers
Nat Advisory Committee Aeronautics -- Report
1944
16 pages
Report
English
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