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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
open access

An Investigation of Aircraft Heaters 14: Performance of Two Finned-Type Crossflow Exhaust Gas and Air Heat Exchangers

Description: Report presenting data on the thermal performance and the static pressure drop characteristics of two finned-type exhaust gas and air heat exchangers. One heater was constructed of copper and stainless steel while the other was constructed from aluminum alloy. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date: August 1944
Creator: Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M. & Sloggy, L. J. B.
Partner: UNT Libraries Government Documents Department
open access

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
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An Investigation of Aircraft Heaters 8: A Simplified Method for the Calculation of the Unit Thermal Conductance Over Wings

Description: Report presenting a simplified approximate method of calculating the unit thermal conductance along an airfoil as a function of distance from the leading edge, by use of heat transfer data for smooth cylinders and smooth flat plates. Several examples are used in order to show the effectiveness of the method.
Date: March 1943
Creator: Martinelli, R. C.; Guibert, A. G.; Morrin, E. H. & Boelter, L. M. K.
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
open access

An investigation of aircraft heaters 16: determination of the viscosity of exhaust gases from a gasoline engine

Description: Report presenting an investigation which found that the absolute viscosity of exhaust gases from a gasoline engine was measured at a range of temperatures and compositions. Results regarding preliminary runs, calibration runs at room temperature, check runs at medium temperatures, and exhaust gas measurements are provided.
Date: June 1944
Creator: Boelter, L. M. K. & Sharp, W. H.
Partner: UNT Libraries Government Documents Department
open access

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

An investigation of aircraft heaters 20: measured and predicted performance of a finned-type cast-aluminum crossflow exhaust gas and air heat exchanger

Description: Report presenting data on the thermal performance and static pressure drop of a finned-type cast-aluminum exhaust gas and air heat exchanger. Results regarding heat transfer, isothermal pressure drop, and heater surface temperature are provided.
Date: April 1945
Creator: Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M.; Romie, F. E. & Sanders, V. D.
Partner: UNT Libraries Government Documents Department
open access

The effect of concentrated loads on flexible rings in circular shells

Description: Report presenting a method of making strain measurements on a series of circular cylinders with reinforcing rings, subjected to concentrated loads, in which the bending stiffness of the rings was varied systematically over a wide range. Results regarding the general remarks, bending-moment coefficient, and skin shear coefficients are provided.
Date: December 1945
Creator: Kuhn, Paul; Duberg, John E. & Griffith, George E.
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
open access

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
open access

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
open access

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

Wind-Tunnel Investigation of Control-Surface Characteristics 21: Medium and Large Aerodynamic Balances of Two Nose Shapes and a Plain Overhang Used With a 0.40-Airfoil-Chord Flap on an NACA 0009 Airfoil

Description: Report discusses the results of an investigation of an NACA 0009 airfoil with a 40-percent-chord flap with medium and large aerodynamic balances of elliptical and blunt nose shapes and a plain overhang. The results are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed and unsealed.
Date: March 1945
Creator: Riebe, John M. & Church, Oleta
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 22: Medium and Large Aerodynamic Balances of Two Nose Shapes and a Plain Overhang Used With a 0.20-Airfoil-Chord Flap on an NACA 0009 Airfoil

Description: "Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an el… more
Date: June 1945
Creator: Riebe, John M. & McKinney, Elizabeth G.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 20: Plain and Balanced Flaps on an NACA 0009 Rectangular Semispan Tail Surface

Description: Correlation is established between aerodynamic characteristics of control surfaces in two-dimensional and three-dimensional flow. Slope of lift curve was affected little by overhang and balance-nose shape, but increased by sealing flap-nose gap. Effectiveness of balancing tab was same for sealed plain flap and unsealed overhang flap. Changes in hinge-moment coefficient were diminished by sealing gap. Values measured by three-dimensional flow disagreed with two-dimensional flow values until aspe… more
Date: October 1944
Creator: Garner, I. Elizabeth
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Rounded Horns and of Guards on a Horizontal Tail Surface

Description: Report discussing an investigation of the aerodynamic effects of horn balances with various plan forms and of guards on a horizontal tail surface. Rounding the adjacent horn and stabilizer edges causes negligible changes to aerodynamic effects except for the area moment of the horn. A solid horn guard mounted on the end of the stabilizer was found to increase the rate of change of lift with angle of attack and elevator deflection.
Date: October 1944
Creator: Liddell, Robert B. & Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department
open access

Effect of fabric deflection at high speeds on the aerodynamic characteristics of the horizontal tail surface of an SB2D-1 airplane

Description: Report presenting an investigation of a full-scale horizontal tail surface to determine the elevator-fabric deflection at high speeds and the aerodynamic effects of the fabric deflection. Two fabric-covered elevators differing only in rib spacing and a solid wooden elevator were tested. Results regarding fabric deflection and aerodynamic characteristics are provided.
Date: June 1945
Creator: Schueller, Carl F.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 14: NACA 0009 Airfoil With a 20-Percent-Chord Double Plain Flap

Description: Report discusses the results of force testing of the aerodynamic characteristics of an NACA 0009 airfoil with a double plain flap; it consisted of a plain forward flap with a chord 20 percent of the airfoil chord and a plan rearward flap with a chord 15 percent of the airfoil chord. Comparisons were made to the characteristics of a 0.50c single plain flap. The lift, hinge moments, drag, and pitching moments are described.
Date: June 1943
Creator: Sears, Richard I. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane 1: Measurements of Flying Qualities With Original Tail Surfaces

Description: Report presenting a series of tests of the Brewster XSBA-1 airplane conducted to determine the effect of various tail modifications. The current report describes an investigation of flying qualities of the airplanes with its original tail surfaces. Testing regarding longitudinal stability and control and stalling characteristics are provided.
Date: June 1943
Creator: Phillips, W. H. & Nissen, J. M.
Partner: UNT Libraries Government Documents Department
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