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Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range

Description: Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. Two airfoils fluttered at a Mach number of 0.85, a third airfoil fluttered at a Mach number of 1.03, and a fourth fluttered at a Mach number of 1.07. Results of calculations of flutter speed using incompressible and compressible air-force coefficients, including a Mach number of 1.0, are presented.
Date: January 1957
Creator: Lauten, William T., Jr. & Nelson, Herbert C.
Partner: UNT Libraries Government Documents Department

Note on flutter of a 60 degree delta wing encountered at low-supersonic speeds during the flight of a rocket-propelled model

Description: From Summary: "An analysis of the flight time history of a rocket-propelled model of a 60 degree delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented."
Date: May 14, 1951
Creator: Lauten, William T., Jr. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department

Flutter investigation on the high subsonic and transonic speed range on cantilever delta-wing plan forms with leading-edge sweepback of 60 degrees, 53 degrees 8', and 45 degrees

Description: Report presenting results of flutter testing on three cantilever delta-wing plan forms at a range of Mach numbers. The time and location of flutter and results of the flutter calculations are provided for each of the wings.
Date: January 31, 1957
Creator: Lauten, William T., Jr. & Burgess, Marvin F.
Partner: UNT Libraries Government Documents Department

Investigation of an all-moveable control surface at a Mach number of 6.86 for possible flutter

Description: From Summary: "Results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane are presented herein. Tests at a Mach number of 6.86 were made on the scaled model and on several other configurations having lower stiffness. Flexibility influence coefficients and calculated modes and frequencies for the weakest configuration are presented."
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Partner: UNT Libraries Government Documents Department

Free-flight tests of 45 degree swept wings of aspect ratio 3.15 and taper ratio 0.54 to measure wing damping of the first bending mode and to investigate the possibility of flutter at transonic speeds

Description: Report presenting free-flight tests made on two pairs of wings of aspect ratio 3.15, taper ratio 0.54, and 45 degrees sweepback in the transonic speed range to measure wing damping and to investigate the possibility of flutter. Results regarding the flight test and analysis and discussion are provided.
Date: October 12, 1954
Creator: O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds

Description: Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.
Date: October 12, 1954
Creator: O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight flutter tests in the transonic and low supersonic speed range of three low-aspect-ratio swept, tapered wings on rocket-propelled vehicles

Description: Report presenting flutter data obtained with the use of rocket-propelled vehicles in the transonic and low supersonic speed ranges for three low-aspect-ratio, highly tapered, swept wings. Structural influence coefficients were obtained for each of the three plan forms and calculated mode shapes and frequencies are provided. Time histories for each of the configurations also demonstrate the flutter pattern of each wing.
Date: March 19, 1956
Creator: Lauten, William T., Jr. & O'Kelly, Burke R.
Partner: UNT Libraries Government Documents Department

Transonic-flutter investigation of wings attached to two low-acceleration rocket-propelled vehicles

Description: Two low-acceleration transonic-flutter vehicles were launched and flown. The first carried two test wings, one of which fluttered at M = 0.92 at a frequency of 61.4 cycles per second. The reference flutter speed determined from two-dimensional theory for an unswept wing in incompressible flow is conservative when compared to the experimental flutter speed. The second vehicle carried two test wings, one of which failed at M = 0.71 because of low-frequency divergent oscillation. Since this failure was not caused by conventional flexure-torsion flutter, no comparison with a reference flutter speed can be made.
Date: November 23, 1948
Creator: Lundstrom, Reginald R.; Lauten, William T., Jr. & Angle, Ellwyn E.
Partner: UNT Libraries Government Documents Department

Free-flight tests of three 1/9-scale models of the wing-ram-jet configuration of the Grumman XSSM-N-6A (Rigel) missile to investigate the possibility of flutter: TED No. NACA DE 223

Description: Report presenting cold-flow free-flight tests at zero lift to investigate the possibility of flutter of simulated wing-ram-jet-nacelle configurations which were 1/9-scale models of the wing and ramjet nacelles of the Grumman XSSM-N-6a missile. Testing was performed on three different configurations. Results regarding Mach number, velocity, aerodynamic density, and flutter are provided.
Date: April 14, 1953
Creator: O'Kelly, Burke R. & Lauten, William T., Jr.
Partner: UNT Libraries Government Documents Department