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Cooling Effects of an Airplane Equipped With an NACA Cowling and a Wing-Duct Cooling System
Report presenting cooling tests of a Northrop A-17A attack airplane equipped with a conventional NACA cowling and then with a wing-duct cooling system. Ground cooling for the wing-duct system without cowl flap was better than for the cowling with flap, but was improved by installing a cowl flap. Satisfactory temperatures were maintained in climb and high-speed flight, but a greater quantity of cooling air was needed for the wing-duct system.
Date:
June 1941
Creator:
Turner, L. I., Jr.; Bierman, David & Boothby, W. B.
System:
The UNT Digital Library
The Effect of Methods of Testing on the Ultimate Loads Supported by Stiffened Flat Sheet Panels Under Edge Compression
Note presenting testing of two series of stiffened flat sheet specimens tested under edge compression using various end conditions: round ends, flat ends, and continuous panels. The specimens consisted of aluminum-alloy flat sheet stiffened by three hat-shaped extruded aluminum-alloy stiffeners. The results indicated that the length of the specimen has an insignificant effect on the ultimate compressive load.
Date:
June 1941
Creator:
Holt, Marshall
System:
The UNT Digital Library
Effects of Some Present-Day Airplane Design Trends on Requirements for Lateral Stability
Note presenting computations made to determine the effects of some airplane design trends on the fin area and the dihedral angle required for lateral stability. The specific factors studied were wing loading, moments of inertia in roll and yaw, wing chord, and tail length. The results of the computations are presented in the form of diagrams of variations of fin area with dihedral angle for neutral stability.
Date:
June 1941
Creator:
Bamber, Millard J.
System:
The UNT Digital Library
Preliminary Stability and Control Tests in the NACA Free-Flight Wind Tunnel and Correlation With Full-Scale Flight Tests
Note presenting a study of stability and control of airplanes by means of dynamic scale models in the 12-foot free-flight wind tunnel. Tests of a scale model of the F-36A airplane were used to develop the testing technique and to afford a comparison of tests of a model in the tunnel with flight tests of the corresponding airplane. Results regarding longitudinal stability and control and lateral stability and control are provided.
Date:
June 1941
Creator:
Shortal, Joseph A. & Osterhout, Clayton J.
System:
The UNT Digital Library
The theoretical lateral motions of an automatically controlled airplane subjected to a yawing moment disturbance
Report presenting an investigation of the lateral motion resulting from a disturbance of the type produced by asymmetric loss of thrust for a hypothetical average airplane equipped with an automatic pilot. Plots of the resultant motion and various modes that constitute the motion are presented for fixed controls and for various amounts of autopilot.
Date:
June 1941
Creator:
Imlay, Frederick H.
System:
The UNT Digital Library