1952•NASA STI Repository (National Aeronautics and Space Administration)Open access
Longitudinal frequency-response characteristics of the Douglas D-558-I airplane as determined from experimental transient-response histories to Mach number of 0.90
Ellwyn E Angle, E. C. Holleman
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Abstract
a t i o n s o f t h e a i r p l a n e i n response to elevator pulses were-obtained over a Mach number range of 0.52 t o .O .go a t a l t it u b s between 30,003 and 37,000 feet.'Through an a p p l i c a t i o n of t h e Fourier transform t o the experimental input and output functions, the longitudinal frequency response of the airplane was determined as a function of Mach number.A comparison of the responsedata estimated from wind-tunnel data with the experimental results showed good agreement.It was found that t h e maximum response a m p l i t u d e w a s a minimum .a t a Mach number of 0.88.A t lower Mach numbers (0.52 .to0.66) t h e .e f f e c t s of lift c o e f f i c i e n t on frequency response were indicated.. .-
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