DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
AD0068899
Title:
A STUDY OF SERVICE-IMPOSED MANEUVERS OF FOUR JET FIGHTER AIRPLANES IN RELATION TO THEIR HANDLING QUALITIES AND CALCULATED DYNAMIC CHARACTERISTICS
Corporate Author:
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC
Report Date:
1955-08-15
Abstract:
Results from a flight program conducted to obtain information on the airplane response and actual rates and amounts of control motion used by service pilots in performance of squadron operational training missions with jet fighter airplanes are correlated with the airplane handling qualities and calculated maximum dynamic response. The correlation indicates that the service pilots in general made use of the static capabilities of their airplanes over most of the speed range as limited either by the control stops or control forces. The maximum responses measured in these service training operations, however, were considerably less than the maximum calculated dynamic response. In longitudinal maneuvers, it is indicated that the pilots have a tendency to maneuver the airplane near its natural frequency. From the results of the calculations of maximum dynamic response for the North American F-86 airplane, it is indicated that pitching accelerations greater than 16 radians per second per second are theoretically within the range of the pilot and airplane capabilities, whereas the highest value obtained in the tests was about 2 radians per second per second. For lateral maneuvers the calculations indicate that the highest vertical tail loads for the F-86 airplane could generally be obtained in fishtail maneuvers however, the calculations indicate that, if rolling pull-out maneuvers were made near the maximum lift coefficient, the vertical-tail loads obtained could be greater than those obtained in fishtail maneuvers. The transverse load factors measured in the present tests were much less than those theorctically obtainable.
Pages:
0057
File Size:
1.93MB
