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Transonic static and longitudinal stability characteristics of low fineness ratio, blunted cylinder reentry body with converging cone afterbody
X-15 aircraft static longitudinal, directional, and lateral stability and control at hypersonic speeds
Dynamic longitudinal and directional stability parameters for spinning body of revolution with high fineness ratio, at transonic speeds
Transonic wind tunnel study of static longitudinal and lateral stability and control characteristics and drag rise of fighter aircraft
Aircraft longitudinal stability with autopilot having time delay
Flight test with large helicopter showing trends of lateral and longitudinal control response with size
Transfer function analysis of fluid contained in longitudinally excited thin-wall cylindrical tank
Force tests to determine static and dynamic longitudinal stability derivatives of powered scale model of tilt-wing V/STOL transport aircraft
Two-stream instability for longitudinal waves in plasma traversed by ion beam
Static longitudinal aerodynamic characteristics of high drag planetary entry bodies
Dynamic longitudinal stability of aircraft in constant glide path angle
Interaction of longitudinal, surface, and transverse waves on plasma boundary
Surface instability and disintegration of liquid in longitudinally excited container
Dynamics tests of engine-structure coupled longitudinal oscillations of Atlas Centaur Surveyor
Liquid discharge from cylindrical container exposed to longitudinal vibration, noting flow retardation
Time and space development equations for longitudinal and transverse modes in Vlasov plasma
Results are presented of tests conducted in the Langley stability tunnel to determine the effects of various components and combinations of components on the static longitudinal and lateral stability characteristics at low speed of a series of 45 degree sweptback-midwing-airplane configurations having wings with an aspect ratio of 2, 4, or 6. The tests were made at a dynamic pressure of 24.9 pounds per square foot which corresponds to a Mach number of 0.13 and Reynolds numbers of 1.00 x 10(exp 6), 0.71 x 10 (exp 6), and 0.58 x 10 (exp 6) based on the respective wing mean aerodynamic chords. The angle-of-attack range covered was from -4 degrees to 32 degrees and the sideslip angles used for the lateral-derivative tests were 5 degrees and -5 degrees. An increasing loss in tail contribution to directional stability both with increasing wing aspect ratio and increasing angle of attack was found to be a principal cause of all the complete models becoming directionally unstable in the high angle-of-attack range.
Results are given of a wind-tunnel investigation at a Reynolds number of 6.8 x 10(exp 6) to determine the static longitudinal stability characteristics of a 42 degree sweptback wing and fuselage combination with a sweptback horizontal tail. Included are the effects of vertical position of fuselage and tail with respect to wing for several combinations of high-lift and staff-control devices. Also included is the effect of a simulated ground.