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Influence of Loading Condition on Piloting Technique for Spin Recovery for Pursuit Airplanes

Description: Bulletin presenting a discussion of information as to the influence on spins and spin recovery of the wing loading and load distribution of present-day pursuit airplanes. The high wing loadings results in high rates of descent and large control forces for recovery.
Date: June 1942
Creator: Soulé, H. A.
Partner: UNT Libraries Government Documents Department

Test Data on the Shear Strength of Joints Assembled With Round-Head and Brazier-Head Rivets

Description: Report discusses data obtained from testing shear of joints riveted with round-head and brazier-head rivets. The tightness of the rivets is also compared for one value of rivet diameter. The load-displacement curves and comparison of load at various values of permanent displacement are presented for both types of rivets.
Date: June 1943
Creator: Mandel, Merven W. & Schuette, Evan H.
Partner: UNT Libraries Government Documents Department

Resume of Hinge-Moment Data for Unshielded Horn- Balanced Control Surfaces

Description: Report summarizes the available hinge-moment data for unshielded horn-balanced control surfaces. The purpose is to correlate the available data to assist with estimating the balance characteristics for use in the design and alteration of control surfaces with horn balances. Plan forms and variation of incremental hinge-moment-coefficient slopes with balance coefficients are presented.
Date: June 1943
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department

Tests of 10-Inch 24S-T Aluminum-Alloy Shear Panels With 1-1/2-Inch Holes

Description: Report discusses the results of testing on "10-inch shear panels of 24S-T aluminum alloy with 1.5 inch holes to determine the stress concentration at static rupture and the deformation characteristics" (from Summary). The strength of the perforated specimens is compared to the solid specimens and the critical stresses are computed. The stress at which permanent set occurs was also measured.
Date: June 1943
Creator: Kuhn, Paul & Levin, L. Ross
Partner: UNT Libraries Government Documents Department

Cylinder-Head Cooling by Means of a Shield in the Exhaust Passage

Description: "Tests were run on a single-cylinder, air-cooled engine with a Wright C9GC cylinder to determine the improvement in cylinder-head cooling that can be obtained by building into the exhaust passage an insulating shield designed to protect the valve-guide boss and the exhaust-passage walls from the exhaust gas. The test results showed an appreciable improvement in cooling of the exhaust-valve-guide boss, of the guide bushing, and of the valve seat" (p. 1).
Date: June 1944
Creator: Wilsted, H. D. & Mulcahy, B. A.
Partner: UNT Libraries Government Documents Department

A Study of the Tightness and Flushness of Machine-Countersunk Rivets for Aircraft

Description: Bulletin presenting the results of an investigation to determine possible improvements in the tightness and the flushness of machine-countersunk rivets. Specimens used in the study were simple lap joints made by different riveting methods. The results indicate that a comparison of the quality of machine-countersunk riveted joints on the basis of maximum load alone is not justified.
Date: June 1942
Creator: Lundquist, Eugene E. & Gottlieb, Robert
Partner: UNT Libraries Government Documents Department

Determination From Flight Tests of Thrust Coefficients for 10 Full-Scale Airplanes in the Gliding Condition With Engine Idling

Description: "Typical thrust and torque coefficients and increments, due to the propeller, in the ratio of the dynamic pressure at the tail to the free-stream dynamic pressure are presented for 10 full-scale airplanes. Calculations indicate that an error of about 2 percent mean aerodynamic chord appears possible in determining the neutral point from wind-tunnel tests or a model in the gliding condition if the propeller is operated at zero thrust rather than at the values of thrust coefficient indicated by the flight tests" (p. 1).
Date: June 1945
Creator: Talmage, Donald B.
Partner: UNT Libraries Government Documents Department

Calculation of Stick Forces for an Elevator With a Spring Tab

Description: "Formulas for the calculation of hinge-moment characteristics of an elevator with a spring tab have been developed in terms of basic aerodynamic parameters, spring stiffness, and airspeed. The formulas have been used in a study of the stick-force gradients on a pursuit airplane equipped with an elevator with a spring tab. Charts are presented showing the variation of stick-force gradient in accelerated flight over a large range of speed and the complete range of spring stiffness for various center-of-gravity locations, altitudes, and airplane sizes" (p. 1).
Date: June 1944
Creator: Greenberg, Harry
Partner: UNT Libraries Government Documents Department

An Investigation of the Characteristics of a Propeller Alcohol Feed Ring

Description: Report discusses the results of an investigation to compare the discharge characteristics of an alcohol feed ring and a standard alcohol discharge nozzle when utilized to supply anti-icing alcohol to the propeller-blade feed shoes on a Curtiss-Wright C-46 cargo airplane. The equipment used, testing practices, and results of the alcohol flow distribution are described.
Date: June 1944
Creator: Neel, Carr B., Jr.
Partner: UNT Libraries Government Documents Department

Application of Balancing Tabs to Ailerons

Description: Analysis was made to determine characteristics required of a balancing-tab system for ailerons in order to reduce aileron stick forces to any desired magnitude. Series of calculations based on section data were made to determine balancing-tab systems of various chord tabs and ailerons that will give, for a particular airplane, zero rate of aileron hinge moment with aileron deflection and yet will produce same maximum rate of roll as a plain unbalanced 15-percent chord aileron of same span. Effects of rolling velocity and of forces in tab link on aileron hinge moments have been included.
Date: June 1942
Creator: Sears, Richard I.
Partner: UNT Libraries Government Documents Department