最近の飛行機のスピン特性とその推測について

抄録

A qualitative investigation of effects of recent design trends of fighter type aircraft is shortly made. Then several existing empirical criteria for spin and recovery characteristics are critically studied and their applicability to the contemporary airplanes proves generally insufficient. T. H. KERR'S criterion seems, however, to succeed to some extent in obtaining reasonable parameters, and it is strongly expected from the standpoint of designer to improve this statistical criterion to correlate better with recent airplanes. At the final part of this report an analytical spin investigation of a jet trainer is illustrated and compared with flight test results. The equations of motion of six degrees of freedom are numerically solved using a digital computer. The aerodynamic derivatives used for calculation are estimated from the wind-tunnel force test results covering angle of attack range of 5 to 90 degrees and side slip angle up to 39 degrees. The comparison between calculated and flight test results indicates fairly good agreement as for the yawing velocity which is the most essential quantity characterizing the spinning motion of aircraft.