EFFECTS OF FUSELAGE NOSE LENGTH AND A CANOPY ON THE STATIC LONCITUDINAL AND LATERAL STABILITY CHARACTERISTICS OF 45° SWEPTBACK AIRPLANE MODELS HAVING FUSELAGES WITH SQUARE CROSS SECTIONS

摘要

A wind-tunnel investigation, was made at low speed in the Langley stability tunnel to determine the effects of fuselage nose length (the fuselage fineness ratio varied from 7.41 to 10.l8) and a canopy on the static longitudinal and lateral stability characteristics of a complete model having a fuselage with square cross sections, a 450 sweptback wing of aspect ratio 3 mounted low on the fuselage, and a 45° sweptback hori?zontal tallow aspect ratio 4 mounted slightly above the wing chord plane. The data were obtained through an angle-of -attack range of -10° to 32 and an angle-of-sideslip range of -24° to 240.