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Analysis of Wind-Tunnel Stability and Control Tests in Terms of Flying Qualities in Full-Scale Airplanes

Description: From Summary: "The analysis of results of wind-tunnel stability and control tests of powered airplane models in terms of the flying qualities of full-scale airplanes is advocated. In order to indicate the topics upon which comments are considered desirable in the report of a wind-tunnel stability and control investigation and to demonstrate the nature of the suggested analysis, the present NACA flying-qualities requirements are discussed in relation to wind-tunnel tests. General procedures for … more
Date: October 1943
Creator: Kayten, Gerald G.
Partner: UNT Libraries Government Documents Department
open access

Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Description: Report presenting a theory regarding engine-cooling variables from a previous report, which was used as a basis for the development of a semi-empirical equation to correlate exhaust-valve temperature with engine conditions. Results regarding the determination of constants, influences of operating variables on mean effective gas temperatures, thermal-resistance factor, and accuracy of correlating equation are provided.
Date: October 1945
Creator: Zipkin, M. A. & Sanders, J. C.
Partner: UNT Libraries Government Documents Department
open access

Fluid de-icing tests on a Chandler-Evans 1900 CPB-3 carburetor mounted on a Pratt & Whitney R-1830-C4 intermediate rear engine section

Description: Report presenting an investigation of the icing and de-icing characteristics of a Pratt & Whitney R-1830 engine induction system. The current report covers a program to determine the most effective rate and method of injection of de-icing fluid to remove a heavy ice formation from the induction system. Results regarding the flow rates, recovery times, de-icing portions of the runs, and ice formation characteristics are provided.
Date: October 1944
Creator: Galvin, Herman B. & Essex, Henry A.
Partner: UNT Libraries Government Documents Department
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The Flow of a Compressible Fluid Past a Circular Arc Profile

Description: Report presenting the use of the Ackeret iteration process to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient.
Date: October 1944
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department
open access

Application of Spring Tabs to Elevator Controls

Description: Report presenting equations for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of the satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling, and to prevent flutter.
Date: October 1944
Creator: Phillips, William H.
Partner: UNT Libraries Government Documents Department
open access

A laboratory investigation of the icing characteristics of the Bendix-Stromberg carburetor model PD-12F5 with the Pratt and Whitney R-1830-C4 intermediate rear engine section

Description: Report presenting icing tests on a Bendix-Stromberg PD-12F5 carburetor mounted on a Pratt & Whitney R-1830-C4 intermediate rear engine section. Limiting icing conditions were established for simulated cruising power and simulated rated power over a range of carburetor-air temperatures, and relative humidities are provided.
Date: October 1944
Creator: Galvin, Herman B. & Essex, Henry A.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Description: Report presenting an investigation in the 19-foot pressure tunnel of two-tapered wings with NACA 230-series airfoil sections, straight leading edges, and constant-chord center sections. Lift, drag, and pitching-moment coefficients were determined for the plain wing and for each flap arrangement for a range of Reynolds numbers. The results indicated that the wing with the square center section has greater maximum lift coefficients and increments of maximum lift due to flap deflections than the w… more
Date: October 1943
Creator: Fairbanks, Richard W. & Alexander, Sidney R.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of an NACA 23021 Airfoil With a 0.32-Airfoil-Chord Double Slotted Flap

Description: Report discusses an investigation to determine the aerodynamic section characteristics of an NACA 23021 airfoil with a double slotted flap with a chord 32 percent of the airfoil chord with the flaps at various positions. The maximum section lift coefficient, profile-drag coefficient, flap positioning, and effects of deflecting or removing the lower lip are described.
Date: October 1944
Creator: Fischel, Jack & Riebe, John M.
Partner: UNT Libraries Government Documents Department
open access

Wind tunnel investigation of a plain aileron with various trailing-edge modifications on a tapered wing 2: ailerons with thickened and beveled trailing edges

Description: Report presenting an investigation in the 7- by 10-foot tunnel of various modifications to the trailing edge of a 0.155-chord plain aileron on a semispan model of the tapered wing of a fighter airplane. The stick forces and rates of roll were estimated for a fighter airplane with the plain and modified ailerons.
Date: October 1942
Creator: Rogallo, F. M. & Purser, Paul E.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Boundary-Layer and Profile-Drag Characteristics of Smooth Wing Sections of a P-47D Airplane

Description: "In Mach range of 0.25 - 0.69, boundary-layer measurements were made on upper wing surface at 25% semi-span, pressure-distribution measurements made on upper surface at 63% semi-span, and wake surveys made at 63% semi-span. The minimum profile-drag coefficient of 0.0062 was indicated for smooth section at 63% semi-span. Critical mach number was exceeded by 0.04, but no compressibility shocks appeared. In slipstream, boundary layer transition occurred as far back as 20% chord on upper surface at… more
Date: October 1945
Creator: Zalovcik, John A.
Partner: UNT Libraries Government Documents Department
open access

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
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
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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
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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

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

Stresses Around Rectangular Cut-Outs in Skin-Stringer Panels Under Axial Loads 2

Description: "Cut-outs in wings or fuselages produce stress concentrations that present a serious problem to the stress analyst. As a partial solution of the general problem, this paper presents formulas for calculating the stress distribution around rectangular cut-outs in axially loaded panels. The formulas are derived by means of the substitute-stringer method of shear-lag analysis" (p. 1).
Date: October 1943
Creator: Kuhn, Paul; Duberg, John E. & Diskin, Simon H.
Partner: UNT Libraries Government Documents Department
open access

Notes on the propeller and slipstream in relation to stability

Description: Report presenting charts and formulas in convenient form for use in the computation of the effects of propellers on stability. Formulas are given for the contributions of the direct propeller forces to the airplane pitching moment, yawing moment, and shift in neutral point due to power.
Date: October 1944
Creator: Ribner, Herbert S.
Partner: UNT Libraries Government Documents Department
open access

Tensile Tests of NACA and Conventional Machine-Countersunk Flush Rivets

Description: An investigation was conducted to determine and compare the tensile strength of NACA and conventional machine-countersunk flush rivets of several rivet-head angles and varying countersunk depth. The results of the investigation are presented in the form of curves that show the variation of the tensile strength of the rivet with the ratio of the sheet thickness to the rivet diameter. For the same rivet-head angle and for a given angle of c/d, the NACA rivets developed higher tensile strength tha… more
Date: October 1944
Creator: Bartone, Leonard M. & Mandel, Merven W.
Partner: UNT Libraries Government Documents Department
open access

Development of Cowling for Long-Nose Air-Cooled Engine in the NACA Full-Scale Wind Tunnel

Description: "An investigation of cowlings for long-nose radial engines was made on the Curtiss XP-42 fighter in the NACA full-scale wind tunnel. The unsatisfactory aerodynamic characteristics of all the cowlings with scoop inlets tested led to the development of the annular high-velocity inlet cowlings. Tests showed that ratio of cooling-air velocity at cowling inlet to stream velocity should not be less than 0.5 for this type of cowling and that critical compressibility speed can be extended to more than … more
Date: October 1941
Creator: Silverstein, Abe & Guryansky, Eugene R.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Air Flow in Right-Angle Elbows in a Rectangular Duct

Description: Report presenting testing on elbow shapes in airplane carburetor air intake ducts with low losses and good velocity distribution without the use of turning vanes. Results regarding the flow coefficient, velocity distribution, and comparison of a variety of elbow ducts are provided.
Date: October 1941
Creator: McLellan, Charles H. & Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department
open access

Performance Comparison of Two Deep Inducers as Separate Components and in Combination With an Impeller

Description: Report presenting testing of two deep inducers as separate components and in combination with an impeller as part of an investigation to correlate design requirements of inducers and impellers. Both inducers, when tested as separate components at a speed corresponding to an impeller tip speed of 1000 feet per second, had a peak adiabatic efficiency of approximately 82 percent. Results regarding the inducers as separate components, inducer-impeller units, and a comparison of inducer performance … more
Date: October 1945
Creator: Ritter, William K.; Ginsburg, Ambrose & Beede, William L.
Partner: UNT Libraries Government Documents Department
open access

The Hydrodynamic Lubrication of Near-Infinite Sliders Such as Piston Rings

Description: "The lubrication of a piston ring is treated as though the ring were a rigid slider of finite width. An expression is obtained for pressure distribution which takes into account the effect of oil leakage from the ends of the ring and which has the convenient form of an end correction to the pressure-distribution formula for an infinite slider. The important formulas are summarized for convenience and two examples are included of their use in finding the pressure pattern over wide sliders" (p. 1… more
Date: October 1944
Creator: Boegli, Charles P.
Partner: UNT Libraries Government Documents Department
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