Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.

Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.

Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.

Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.

"An investigation has been made in the Langley Unitary Plan wind tunnel at Mach numbers of 1.60, 1.80, and 2.00 to determine the aerodynamic characteristics of a 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, rudder, and aileron, as well as the vertical-tail-load characteristics. Although the data are presented without analysis, a limited inspection of the longitudinal control results indicates a loss in maximum lift-drag ratio due to trimming of about 1.8 because of the large static margin" (p. 1).

Memorandum presenting a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation is to be considered preliminary in that only estimated airplane properties were available for the scaling. Results regarding interpretation of results, presentation of data, and a discussions are provided.

Memorandum presenting the performance of a variable-internal-contraction inlet without boundary-layer removal measured at Mach numbers of 2.00, 2.50, and 2.92. The total-pressure recovery at the design Mach number, 2.50, was 0.78. Results regarding total-pressure recovery and contraction ratio, flow unsteadiness and distortion, and summary data correlations are provided.

Report presenting the effects at Mach number 2.01 of various changes in nose and afterbody shape on the static aerodynamic characteristics of a body of revolution with a fineness ratio of 11 with an ogive nose, a cylindrical center section, and a boattail or cylindrical afterbody. Some body conditions were tested in combination with a vertical tail. Results regarding the effects of nose and afterbody modifications and vertical tail-on configurations are provided.

Report presenting a transonic flutter investigation of models of the wing of a fighter airplane. Results regarding the wings with and without leading-edge chord-extensions, and scaling of the stiffness are presented. The flutter boundary was found to remain below sea level with or without the leading-edge extensions.

Report presenting an investigation to determine the effects on performance of positioning normal shocks in or upstream of both a long and a short subsonic annular diffuser. Results regarding the entrance flow conditions, performance for subsonic-entrance flows, and performance with choked- and supersonic-entrance flows are provided.

A wind-tunnel investigation to determine the effects of both single and twin jets on base drag of a cylindrical body has been conducted at Mach numbers from 0.6 to 1.4. The plane of the jet exit was varied with respect to that of the afterbody. Jet total-pressure ratio ranged up to 20. Significant improvements in base drag were obtained by extending the plane of the jet exits beyond the afterbody base and by venting the base cavity to the external stream.

Report presenting results for a canard bomber-type configuration designed for supersonic cruise flight at Mach numbers 2.50 and 2.87 and over a range of angles of attack and angles of sideslip. Results regarding longitudinal characteristics and lateral stability are provided. The original configuration was directionally unstable at low angles of attack, but satisfactory directional stability could be obtained using upper-surface vertical fins.

Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.

Report presenting a wind-tunnel investigation of the low-speed aerodynamic characteristics of an airplane configuration designed to obtain high lift-drag ratios at hypersonic speeds. The power-off landing of this aircraft would be difficult due to the high sinking speeds inherent in the design. Results regarding the longitudinal characteristics, lateral characteristics, and landing considerations are provided.

Report presenting measurements in a wind tunnel of the subsonic static and dynamic-rotary stability derivatives of a model of an airplane designed to fly at high supersonic speeds and high altitudes. The effects of flaps and landing gear, speed brakes, and several model components are included in the results as well as the stability characteristics of the model.

Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment distributions, leading-edge-flap characteristics, and a comparison with wind-tunnel data are provided.

Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Whether the Motor Vehicle Sales Tax levied by Article 7047K, V.C.S., applies where an automobile dealer secures a motor vehicle from a manufacturer to be used by a salesman for demonstration purposes when no consideration is involved?

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: If a vacancy occurs in the office of County Attorney prior to the general election in a year when the office of County Attorney is not up for election, can the vacancy be filled at the next general election and related questions.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: In instances where a District Court has jurisdiction in two counties, may two different probation officers be appointed to each work exclusively in only one county within the Judicial District under the provisions of Art. 781d, V.A.C.C.P. of Texas (Texas Adult Probation and Parole Law of 1957, Acts 1957, 55th Leg., Chapter 226, Page 466)?

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Whether an elector who is within the county of his residence during the period for absentee voting, but who expects to be absent on election day and applies for an absentee ballot on that ground, may vote absentee by mail.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Jurisdiction of Railroad Commission and Department of Public Safety over Motor Carrier and Motor Bus Operations Between Contiguous Incorporated Cities.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Whether or not the Finance Commission of Texas may, under the provisions of Article 342-112, Vernon's Civil Statutes, authorize the expenditure of moneys for costs and other expenses incurred by the State Banking Board in the trial of a case brought under the provisions of Article 342-115, Vernon's Civil Statutes.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Can a Plaintiff who makes a costs deposit pursuant to Rule 146, Texas Rules of Civil Procedure, and later prevails in the trial of his case with all costs assessed against the Defendant from whom the District Clerk cannot collect said costs, recover his costs deposit? If so, what recourse does the District Clerk have in the event portions of the deposit have been paid into the County Treasury?