DESIGN CALCULATIONS ON PROVEN TRAINER AND FIGHTER AIRCRAFT FOR THE VERIFICATION OF A GUST DESIGN PROCEDURE.
Abstract
Design calculations are performed on proven trainer and fighter aircraft for the purpose of verifying a new gust design procedure based on power spectral techniques. The aircraft used in the computation are Northrop Norair T-38 trainer and F-5A fighter. The new gust design procedure uses a gust power spectrum as the input in aircraft response calculation, as against the present discrete gust approach, where the input is a gust velocity profile with a single frequency determined by the aircraft speed and the gust gradient distance. The report describes the specific aircraft weight and flight configurations used in the computation. The choice of stress sensitive locations is explained and illustrated. Also presented is the computation procedure for obtaining the aircraft transfer functions to be used in both the discrete gust and power spectral approaches. Based on the gust input spectrum and the aircraft transfer functions, a number of aircraft gust response power spectra are generated. These latter spectral data are integrated along the frequency band to obtain the mean aircraft response levels and the average zero crossing counts which are the final results of the computation. Through the computation, various scales of turbulence and cut-off frequencies are used to study their effects on the end results of the new gust design procedure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1966
- Accession Number
- AD0800059
Entities
People
- A. K. Cross
- B. D. Kamberg
- Chintsun Hwang
- W. S. Pi