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The Porpoising Characteristics of a Planing Surface Representing the Forebody of a Flying-Boat Hull

Description: Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
Date: May 1942
Creator: Benson, James M.
Partner: UNT Libraries Government Documents Department
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An Investigation of Hydrofoils in the NACA Tank 1: Effect of Dihedral and Depth of Submersion

Description: Tests were conducted on hydrofoil assemblies approximating an arrangement for use under seaplanes or surface boats. A series of hydrofoils, each supported by two struts, was towed at various depths ranging from partial submersions to a depth of 5-chord lengths. At depths greater than 4 or 5 chords, the influence of the surface of the water is small; hydrofoils operating at low speed will have characteristics similar to those of airfoils of the same section.
Date: September 1942
Creator: Benson, James M. & Land, Norman S.
Partner: UNT Libraries Government Documents Department
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The effect of dead rise upon the low-angle type of porpoising

Description: Report presenting data pertaining to forces and moments developed by V-bottom planing surfaces of different angles of dead rise in order to compute the effect of dead rise on the lower trim limit of stability on a seaplane. Increase of angle of dead rise in the range of 10 degrees to 30 degrees causes an important increase in the lower limit of stability.
Date: October 1942
Creator: Benson, James M. & Lina, Lindsay J.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 6: Heat Transfer Equations for the Single Pass Longitudinal Exchanger

Description: Report presenting an analysis of parallel flow and contraflow single pass heat exchangers, together with charts which allow the direct evaluation of the thermal performance of the units without recourse to trail-and-error techniques. The use of equations and charts is illustrated by several examples.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department
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A Preliminary Investigation of the Characteristics of Air Scoops on a Fuselage

Description: Report presenting an investigation of the characteristics of air scoops in the NACA propeller-research tunnel. The investigation showed that, at inlet-velocity ratios equal to or greater than 0.3, scoops in a forward position on the fuselage gave total pressures in the inlet nearly equal to free-stream total pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Drag and Pressure Distribution of Windshields at High Speeds

Description: Report presenting tests in the 8-foot high-speed wind tunnel to determine the loads and the load distributions at high speeds for a number of windshields of the cockpit-canopy type. Ten windshields of various designs similar to those in general use were included in these tests. Results regarding drag, loads, and design considerations are provided.
Date: January 1942
Creator: Delano, James B. & Wright, Ray H.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 5: Theory and Use of Heat Meters for the Measurement of Rates of Heat Transfer Which Are Independent of Time

Description: Report presenting a description of a meter which will measure the heat flowing through surfaces. Its operation is based on the measurement of the temperature decrease through a fixed thermal resistance. Only the case of heat flow independent of time is discussed in this particular report.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of Gun Openings in the Nose of the Fuselage of a 1/4-Scale Model

Description: "In connection with recent tests of a 1/4-scale model pursuit airplane in the NACA 8-foot high-speed tunnel, gun openings having low drag were developed for installation in the nose of the fuselage. The increase in the fuselage-drag coefficient for the final form of openings was 0.0132 at a Mach number of 0.69 and at an angle of attack of 0 degrees. The corresponding drag coefficient based on the wing area was about 0.0005. The critical speed of the airplane was not affected by the gun openings… more
Date: July 1942
Creator: Fedziuk, Henry A.
Partner: UNT Libraries Government Documents Department
open access

A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

Description: Report presenting flight tests made with a modified Ryan ST airplane to determine the effect on aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. With the flaps fully extended, the aileron effectiveness was reduced by approximately 18 percent of the effectiveness measured with ailerons alone.
Date: May 1942
Creator: Williams, W. C.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 2: Properties of Gases

Description: Report presenting the properties of some exhaust gases and air that are pertinent to airplane heat transfer calculations, including air, hydrogen, nitrogen, oxygen, carbon dioxide, and carbon monoxide. A bibliography related to gas properties is also provided.
Date: October 1942
Creator: Tribus, Myron & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 3: Measured and Predicted Performance of Double Tube Heat Exchangers

Description: Report presenting a study of two double tube cylindrical heat exchangers, in which hot exhaust gases pass through the annular space and ventilating air passes through the center tube, to determine heat transfer performance and pressure drop. Tests were performed in order to establish a simple, accurate method of predicting the performance of the double tube heat exchanger, to compare the performance of the straight and dimpled tubes, and to determine the pressure drop across the units.
Date: October 1942
Creator: Martinelli, R. C.; Weinberg, E. B.; Morrin, E. H. & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Aircraft Heaters 4: Measured and Predicted Performance of Longitudinally Finned Tubes

Description: Report presenting a study of two double tube, cylindrical, longitudinally finned heat exchangers in which hot exhaust gases pass through the annular space and ventilating air passes through the center tube in order to determine heat transfer and pressure drop performance.
Date: October 1942
Creator: Martinelli, R. C.; Weinberg, E. B.; Morrin, E. H. & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department
open access

Strength Tests of Thin-Wall Truncated Cones of Circular Section

Description: "The ends of thin-wall truncated cones of circular section were clamped to rigid bulkheads and the cones subjected to strength tests. The results from torsion tests of five, compression tests of three, and tests in combined transverse shear and bending of 18 truncated cones are given herein. The results of the tests are correlated with the previously published results of corresponding tests of circular cylinders and are presented in charts suitable for use in design" (p. 1).
Date: December 1942
Creator: Lundquist, Eugene E. & Schuette, Evan H.
Partner: UNT Libraries Government Documents Department
open access

Preliminary experimental investigation of airfoils in cascade

Description: Report presenting information about airfoils in cascade, including the angle through which the air is turned and where the cascade losses are located.
Date: July 1942
Creator: Kantrowitz, Arthur & Daum, Fred L.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of an NACA full-span high-lift lateral-control combination 1: section characteristics, NACA 23012 airfoil

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel to determine the aerodynamic section characteristics of several arrangements of an NACA full-span high-lift lateral-control combination. The combination consists of a full-span flap of airfoil profile that retracts ahead of a narrow-chord full-span aileron. Results regarding coefficients, precision, plain airfoil, determination of optimum aileron-flap arrangement, section aerodynamic characteristics, and lateral-control charact… more
Date: July 1942
Creator: Rogallo, F. M. & Lowry, John G.
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of the Stability of a Towed Body

Description: Report presenting flight tests to determine whether a towed body that was designed to meet certain specifications met the stability specification, which required that angular deviations in flight should be less than 1 degree. The requirement was met in flight in smooth air, but not in rough air, where the rolling motions were considerably larger.
Date: October 1942
Creator: Phillips, W. H.
Partner: UNT Libraries Government Documents Department
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Full-Scale Tunnel Investigation of the Control and Stability of a Twin-Engine Monoplane With Propellers Operating

Description: Report presenting extensive force tests covering a wide range of propeller thrust coefficients on a typical twin-engine tractor monoplane model with the horizontal tail surface removed and attached. Measurements were made with flaps retracted and deflected at various angles of attack with different stabilizer and elevator settings. Results regarding the effect of propeller operation on wing-fuselage combination and forces and air flow at tail are provided.
Date: November 1942
Creator: Sweberg, Harold H.
Partner: UNT Libraries Government Documents Department
open access

Effect of Changes in Aspect Ratio, Side Area, Flight-Path Angle, and Normal Acceleration on Lateral Stability

Description: Report presenting computations made to determine the effect of changes in wing aspect ratio, additional side area, flight-path angle, and normal acceleration on the relation between the fin area and the dihedral angle required for spiral and for oscillatory lateral stability for a hypothetical airplane of the pursuit or fighter categories. The diagrams indicate that the effect of wing aspect ratio on lateral stability is small.
Date: December 1942
Creator: Bamber, M. J.
Partner: UNT Libraries Government Documents Department
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Tests of a Stressed-Carrying Door in Shear

Description: Bulletin presenting testing of a monocoque box with a stress-carrying door made and tested in torsion. The results indicate that if a stress-carrying door and its frame are made sufficiently heavy, the torsional stiffness of the box with the door can be made greater than the torsional stiffness of the box without the cut-out" (p. 1).
Date: August 1942
Creator: Gottlieb, Robert
Partner: UNT Libraries Government Documents Department
open access

Tests of a Stress-Carrying Door in Compression

Description: Bulletin presenting the results of bending tests on a monocoque box with the door on the compression side. The results indicate that the effectiveness of a stress-carrying door depends on the intended function of the door.
Date: September 1942
Creator: Gottlieb, Robert
Partner: UNT Libraries Government Documents Department
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