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China fights on.

Description: A Chinese man in military uniform and cap looks toward the sky. Several tiny planes circle him. The planes and his cap bear the 12-pointed sun symbol of the Chinese forces. Near the right edge of the poster are four Chinese characters in red. The characters roughly translate as "Unite Against the Enemy and Rebuild Our Nation."
Date: [1941-1946?]
Creator: Gaydos.
Partner: UNT Libraries Government Documents Department

China first to fight! : United China Relief participating in National War Fund.

Description: Color poster of Chinese soldier in a green uniform, walking behind a woman holding the hand of child. Both the woman and child are dressed in plain blue traditional Chinese clothing. The woman's arm is in a sling and a bloody bandage can be seen on her wrist. The poster background is bright yellow.
Date: [1941-1946?]
Creator: Sawyers, Martha, 1902-1988.
Partner: UNT Libraries Government Documents Department

The guys who don't say much.

Description: Black & white poster. At left is an article describing the "average man". At right is a photograph of a man wearing a plaid shirt and plaid jacket, overalls, a cap, and smoking a pipe. Below the photo are "Questions and Answers about Bonds and Stamps".
Date: [1941-1942?]
Partner: UNT Libraries Government Documents Department

Put the squeeze on the Japanese : beat your promise.

Description: A caucasian man representing American workers squeezes a large clamp around a caricature of Hideki Tojo. The worker wears a sleeveless undershirt labeled "Increased Production". His watch says "RCA". A caption behind his hat says "You and I". Tojo appears to be shouting, as illustrated by several (presumably) Japanese characters. He is reaching toward a bloody sword labeled: "Remember Pearl Harbor!" In the background are battleships, firing tanks, flying airplanes, and lightning bolts.
Date: [1941-1942?]
Partner: UNT Libraries Government Documents Department

Stamp 'em out! : beat your promise.

Description: Color poster shows a boot about to stomp on two snakes and a frog with caricatured faces. The pant leg is labeled "You and I". The snakes represent Adolf Hitler and Japan; the frog represents Benito Mussolini.
Date: [1941-1942?]
Creator: Ryling?
Partner: UNT Libraries Government Documents Department

Nonstationary flow about a wing-aileron-tab combination including aerodynamic balance

Description: This paper presents a continuation of the work published in Technical Report no. 496. The results of that paper have been extended to include the effect of aerodynamic balance and the effect of a tab added to the aileron. The aerodynamic coefficients are presented in a form convenient for application to the flutter problem.
Date: December 16, 1941
Creator: Theodorsen, Theodore & Garrick, I. E.
Partner: UNT Libraries Government Documents Department

A study by high-speed photography of combustion and knock in a spark-ignition engine

Description: "The study of combustion in a spark-ignition engine given in Technical Report no. 704 has been continued. The investigation was made with the NACA high-speed motion-picture camera and the NACA optical engine indicator. The camera operates at the rate of 40,000 photographs a second and makes possible the study of phenomena occurring in time intervals as short as 0.000025 second. Photographs are presented of combustion without knock and with both light and heavy knocks, the end zone of combustion being within the field of view" (p. 15).
Date: December 9, 1941
Creator: Miller, Cearcy D.
Partner: UNT Libraries Government Documents Department

Analysis of Ground Effect on the Lifting Airscrew

Description: "A study is presented of ground effect as applied to the lifting airscrew of the type used in modern gyroplanes and helicopters. The mathematical analysis of the problem has been verified by tests made of three rotor models in the presence of a large circular "ground plane." The results of the study are presented in the form of convenient charts" (p. 1).
Date: December 1941
Creator: Knight, Montgomery & Hefner, Ralph A.
Partner: UNT Libraries Government Documents Department

The Calculation of Span Load Distributions of Swept-Back Wings

Description: "Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9" (p. 1).
Date: December 1941
Creator: Mutterperl, William
Partner: UNT Libraries Government Documents Department

Determination of the Bending and Buckling Effect in the Stress Analysis of Shell Structures Accessible From One Side Only

Description: "The present report describes a device for ascertaining the bending and buckling effect in stress measurements on shell structures accessible from one side only. Beginning with a discussion of the relationship between flexural strain and certain parameters, the respective errors of the test method for great or variable skin curvature within the test range are analyzed and illustrated by specimen example" (p. 1).
Date: December 1941
Creator: Dose, A.
Partner: UNT Libraries Government Documents Department

A Flight Investigation of Internally Balanced Sealed Ailerons

Description: "Flight tests were made of a type of internally balanced sealed ailerons installed on a Ryan ST airplane. Aileron effectiveness and stick forces were measured at various airspeeds under NACA recording instruments. For comparison, the aileron characteristics were also determined without the internal balance and seals" (p. 1).
Date: December 1941
Creator: Williams, W. C. & Kleckner, H. F.
Partner: UNT Libraries Government Documents Department

Hydrodynamic Tests of a 1/10-Size Model of the Hull of the Latécoère 521 Flying Boat: NACA Model 83

Description: From Summary: "A 1/10-size model of the hull of the French flying boat Latecoere 521 was tested in the NACA tank. This model is one of a series of models of the hulls of actual flying boats of both foreign and domestic type that are being tested in the NACA tank to provide information regarding the water characteristics of a variety of forms of hull and to illustrate the development of present-day types of flying boat. The lines and the offsets of the hull were obtained from the manufacturer through the Paris office of the NACA."
Date: December 1941
Creator: Olson, Roland E. & Lina, Lindsay J.
Partner: UNT Libraries Government Documents Department

Inertia of Dynamic Pressure Arrays

Description: From earlier measurements and the mathematical examples, it can be gathered that the inertia of dynamic pressure arrays can be computed with sufficient accuracy and the proper size of tubing established, provided that certain requirements are made on the inertia. A new mathematical term, the pneumatic time constant, depends only on the dimensions of the tubing and of the indicator and enables the comparison of different dynamic pressure arrays.
Date: December 1941
Creator: Weidemann, Hans
Partner: UNT Libraries Government Documents Department

Internally Finned Honeycomb Radiators

Description: Report presenting the performance of several internally finned radiators and a comparison with more conventional honeycomb radiators. In a typical case, the new radiator can be designed with 55 percent less volume and 18 percent less power expenditure while dissipating the same amount of heat.
Date: December 1941
Creator: Tifford, Arthur N.
Partner: UNT Libraries Government Documents Department

Lift and Drag Characteristics of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: Report presenting a wooden model equipped with a slotted flap that was tested in the two-dimensional tunnel. It represented a wing section of the Curtiss-Wright P-60A airplane and the NACA 66,2-118 section. Results regarding lift characteristics, drag coefficients, and flap deflection characteristics are provided.
Date: December 1941
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department

Lift and Drag Tests of Three Airfoil Models With Fowler Flaps Submitted by Consolidated Aircraft Corporation

Description: Report presenting lift and drag tests made in the two-dimensional tunnel of three airfoil models. The models represented intermediate sections on alternative wings of the XB-32 airplane and were equipped with 0.30 Fowler flaps. Results regarding the Davis model, the C.A.C. model, and low-drag model are provided.
Date: December 1941
Creator: Abbott, Ira H. & Turner, Harold R., Jr.
Partner: UNT Libraries Government Documents Department

Notes on the Stability and Control of Tailless Airplanes

Description: "Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback" (p. 1).
Date: December 1941
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department

Pressure-Distribution Measurements of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: "Pressure-distribution measurements were made at the request of the Materiel Division, U.S. Army Air Corps, on a 24-inch-chord wooden model equipped with a slotted flap and submitted by the Curtiss-Wright Corporation. The tests were made in the Langley two-dimensional tunnel at a Reynolds number of about 5,600,000" (p. 1).
Date: December 1941
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department

Pressure distribution over an airfoil with a balanced split flap

Description: Report presenting a pressure-distribution investigation conducted in the 4- by 6-foot vertical wind tunnel to determine the air loads on an airfoil with a 22.1-percent-chord balanced split flap. Results regarding section pressure distribution and aerodynamic section coefficients are provided.
Date: December 1941
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department

Stress Analysis of Circular Frames

Description: "The stresses in circular frames of constant bending stiffnesses, as encountered in thin-wall shells, are investigated from the point of view of finite depth of sectional area of frame. The solution is carried out for four fundamental load conditions. The method is illustrated on a worked out example" (p. 1).
Date: December 1941
Creator: Fahlbusch, H. & Wegner, W.
Partner: UNT Libraries Government Documents Department

Tank Tests of a 1/5 Full-Size Dynamically Similar Model of the Army OA-9 Amphibian With Motor-Driven Propellers: NACA Model 117

Description: Report presenting an investigation of the influence of running propellers on the hydrodynamic characteristics of a model of a seaplane in the tank to evaluate the importance of power in tests of dynamically similar models. The powered propellers were found to have a large effect on the aerodynamic characteristics of the model and consequently on the hydrodynamic stability, which depends to a certain extent on these characteristics. Generally, the magnitude of the effects of a given increment of power in such tests decreases as the power is increased.
Date: December 1941
Creator: Parkinson, John B. & Olson, Roland E.
Partner: UNT Libraries Government Documents Department