A Comparison of the Measured and Predicted Lateral Oscillatory Characteristics of a 35 deg. Swept-Wing Fighter Airplane
Abstract
Results of tests of a 35 deg swept-wing fighter airplane, during which lateral oscillations were performed over a Mach number range from 0.41 to 0.79 at a pressure altitude of 10,000 feet and from 0.49 to 1.04 at 35,000 feet, are presented in this report. Experimental and computed values for the period of the lateral oscillation and time required to damp to half amplitude are shown. One sample oscillation time history is included for each test altitude. The airplane was found to be laterally stable, statically and dynamically, throughout the range of speeds tested. At both altitudes, the variation with Mach number of the period of the lateral oscillation was satisfactorily predicted from available and estimated aerodynamic and mass parameters. The time required to damp to half amplitude, as measured from flight at both altitudes, varied with Mach number in essentially the same manner as predicted from computations. The measured damping was somewhat better than that obtained from computations for the altitude of 35,000 feet, particularly at a Mach number of 0.92. An increase in time to damp to half amplitude was noted between Mach numbers of 0.95 and 1.04.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1955
- Accession Number
- ADA377314
Entities
People
- George E. Cooper
- Walter E. Mcneill
Organizations
- National Aeronautics and Space Administration