Lateral Stability Characteristics At Low Lift Between Mach Numbers Of 0 85 And 1 15 Of A Rocket Propelled Model Of A Supersonic Airplane Configuration Having A Tapered Wing With Circular Arc Sections And 40 Degree Sweepback

Lateral Stability Characteristics at Low Lift Between Mach Numbers of 0.85 and 1.15 of a Rocket-propelled Model of a Supersonic Airplane Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback

Free-flight Experience of the Lateral Stability Characteristics at Low Lift of a 45 Degree Swept-wing Rocket-propelled Model Equipped with a Nonlinear Yaw-rate Damper System at Mach Numbers from 0.76 to 1.73

A low-lift lateral stability investigation was conducted with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system in the Mach number range from 0.76 to 1.73. The lateral oscillations due to periodic yawing disturbances were analyzed to determine the lateral characteristics of the airframe-yaw-rate-damper combination. In addition, due to a dead spot in the operation of the yaw-rate damper system, it was possible to determine the lateral derivatives of the model when the Mach number was greater than 1.2 by the use of the time-vector method while the damper was essentially inoperative. The data were further interpreted in terms of full-scale-airplane flying qualities.

Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20

A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.