Resource Type
Serial/Series Title
NACA Wartime Reports
310
NACA Advanced Restricted Reports
119
NACA Memorandum Reports
72
NACA Advanced Confidential Reports
70
Atomic Energy Commission Reports
60
NACA Technical Reports
47
CP (Series) (Chicago, Illinois)
46
Chicago University Reports
46
NACA Restricted Bulletins
42
NACA Technical Notes
41
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Some Effects of Propeller Operation on the Distribution of the Load on the Vertical Tail Surface of a Typical Pursuit Airplane
Report discusses the results of testing on the pressure distribution at several longitudinal sections of the vertical tail surface of the Curtiss P-40K airplane at various angles of attack and angles of yaw and with the propeller removed and propeller operating. Results regarding the chordwise pressure distributions, effects of propeller operation on the spanwise distribution of normal-force coefficient, total normal-force coefficients, and effect of propeller operation on the variation of vertical-tail normal-force coefficients are presented.
Date:
March 1944
Creator:
Sweberg, Harold H. & Dingeldein, Richard C.
Object Type:
Report
System:
The UNT Digital Library
Flutter tests of B-34 fin-rudder-tab system
From Summary: "Tests on the B-34 fin-rudder-tab assembly were performed in the NACA 8-foot high-speed tunnel. Two cases of tab flutter were studied. It was shown conclusively that the frequency of the original or heavy tab was too low and caused coupling with one of the lower bending frequencies. A general conclusion was made that the tab frequency should be considerably higher than the lower modes of the fin-rudder assembly because there is generally a weaker coupling between the tab and the higher mode responses."
Date:
September 1944
Creator:
Theodorsen, Theodore
Object Type:
Report
System:
The UNT Digital Library
Maximum Rates of Control Motion Obtained From Ground Tests
Report discusses the results of testing to determine the maximum rates of control stick (elevator) motion and corresponding maximum stick forces that could be exerted based on experiments with several pilots. The main topics explored were the comparison of the maximum rates of push and pull, maximum rates of push and pull when a mental restriction was placed on the pilot, and maximum rates at which the pilot though he would apply the elevator control forces versus the actual application of forces. Information about experimental procedures and the rig the testing occurred on is included.
Date:
May 1944
Creator:
Beeler, De E.
Object Type:
Report
System:
The UNT Digital Library
Flight tests of various tail modifications on the Brewster XSBA-1 airplane 3: measurements of flying qualities with tail configuration 3
Report presenting a series of tests on the Brewster XSBA-1 airplane to determine the effects of various tail modifications. Some of the modifications include variations of the chord of the elevator and rudder while the span and total area of the surfaces are kept constant and variations of the total area of the vertical tail surface. Results regarding the longitudinal stability and control and lateral stability and control are provided.
Date:
July 1944
Creator:
Crane, H. L. & Reeder, J. P.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of an NACA 23021 Airfoil With a 0.32-Airfoil-Chord Double Slotted Flap
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.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Available Data on Control Surfaces Having Plain-Overhang and Frise Balances
From Introduction: "The present paper deals with control surfaces having plain-overhang and Frise balances."
Date:
May 1944
Creator:
Purser, Paul E. & Toll, Thomas A.
Object Type:
Report
System:
The UNT Digital Library
An Automatically Variable Control Linkage and Its Effect on the Lateral-Control Characteristics of a High-Speed Fighter Airplane
Report discusses an analysis and preliminary design of a control linkage that varies automatically with dynamic pressure. The advantages of the device, including greater lateral control than a fixed control linkage without additional aerodynamic balance, are detailed. The effect of variable linkage on lateral-control characteristics is also described.
Date:
May 1944
Creator:
Gillis, Clarence L.
Object Type:
Report
System:
The UNT Digital Library
Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation
Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.
Date:
September 1944
Creator:
Tetervin, Neal
Object Type:
Report
System:
The UNT Digital Library
Effect of Compressibility on Pressure Distribution Over an Airfoil With a Slotted Frise Aileron
Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees.
Date:
July 1944
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap
Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Date:
December 1944
Creator:
Holtzclaw, Ralph W. & Weisman, Yale
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils From Tests in the NACA Two-Dimensional Low-Turbulence Pressure Tunnel
Report presenting two low-drag airfoils, the NACA 747A315 and the NACA 747A415, which are designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient and are tested in the tow-dimensional low-turbulence pressure tunnel.
Date:
September 1944
Creator:
von Doenhoff, Albert E. & Stivers, Louis S., Jr.
Object Type:
Report
System:
The UNT Digital Library
Drag measurements at high Reynolds numbers of a 100-inch-chord NACA 23016 practical construction wing section submitted by Chance Vought Aircraft Company
Report presenting drag measurements in the two-dimensional low-turbulence tunnel of an available 100-inch-chord model of the NACA 23016 wing section. Results regarding the curves of section drag coefficient plotted against Reynolds number for various surface conditions and lift coefficients, variation of drag coefficient with lift coefficient, and effects of skin friction are provided.
Date:
June 1944
Creator:
von Doenhoff, Albert E. & Nuber, Robert J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Vertical-Tail Loads in Rolling Pull-Out Maneuvers
Bulletin presenting an analysis of the vertical-tail loads to be expected as a result of abrupt aileron action in accelerated flight, as in rolls from turns or pull-outs, for example. Critical tail loads may occur in rolling pull-out maneuvers, particularly on airplanes with good ailerons and low directional stability.
Date:
August 1944
Creator:
Gilruth, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Flight measurements of horizontal tail loads on a typical propeller-driven pursuit airplane during stalled pull-outs at high speed
Report presenting flight measurements of the pressures on the horizontal tail surfaces of a typical propeller-driven pursuit airplane during stalled pull-outs at high Mach number. Unit loads measured on the stabilizer at safe maneuvering limits were not only considerably in excess of the design unit loads, but also occurred in a direction opposite to the design loads. Revision of the tail-load design requirements and manner of specifying safe maneuverability limits to pilots appears necessary.
Date:
April 25, 1944
Creator:
Clousing, Lawrence A. & Turner, William N.
Object Type:
Report
System:
The UNT Digital Library
Estimates of the Vertical-Tail Loads of a Bell P-63A-1 Airplane (AAF No. 42-68889) in Accelerated Rolling Maneuvers Based on Flight Tests With Two Vertical-Tail Arrangements
Report discussing the results of using an enlarged vertical tail on a P-63A-1 on directional stability. The tests included measurements of the amount of sideslip at various speeds and normal accelerations. Potential required modifications for increased performance using the larger tail are also described.
Date:
November 30, 1944
Creator:
Johnson, Harold I.
Object Type:
Report
System:
The UNT Digital Library
Calculation of Stick Forces for an Elevator With a Spring Tab
"Formulas for the calculation of hinge-moment characteristics of an elevator with a spring tab have been developed in terms of basic aerodynamic parameters, spring stiffness, and airspeed. The formulas have been used in a study of the stick-force gradients on a pursuit airplane equipped with an elevator with a spring tab. Charts are presented showing the variation of stick-force gradient in accelerated flight over a large range of speed and the complete range of spring stiffness for various center-of-gravity locations, altitudes, and airplane sizes" (p. 1).
Date:
June 1944
Creator:
Greenberg, Harry
Object Type:
Report
System:
The UNT Digital Library
A method for predicting the elevator deflection required to land
Report presenting a method for predicting from basic airplane characteristics the elevator deflection required to maintain optimum landing attitude. Charts for evaluating the components of the equation for elevator deflection and a comparison of computed and measured values for 15 airplanes are included. The computed deflection is considered the minimum value required to maintain landing attitude due to variations in piloting technique.
Date:
September 1944
Creator:
Goranson, R. Fabian
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel tests of hinge-moment characteristics of spring-tab ailerons
Report presenting testing in the stability tunnel of two types of spring tab used as balances on a partial-span plain aileron. The tabs were connected to a spring located in the control system so that tab deflection was dependent on the control force.
Date:
January 1944
Creator:
Imlay, Frederick H. & Bird, J. D.
Object Type:
Report
System:
The UNT Digital Library
Analysis of available data on the effectiveness of ailerons without exposed overhang balance
From Introduction: "As a part of the general lateral-control investigation by the NACA, the large amount of two- and three-dimensional data on the rolling effectiveness of ailerons without exposed overhang balance is collected and analyzed in the present paper."
Date:
May 1944
Creator:
Crandall, Stewart M. & Swanson, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Collection of Balanced-Aileron Test Data
"Test data of balanced ailerons have been collected from NACA and British sources. These data, which are presented in the form of charts, are grouped as A - ailerons with Frise balances, B - ailerons with blunt-nose balances, C - ailerons with internal balances, D - ailerons with contour modifications, and E - ailerons with tabs. Results of flight tests and of wind-tunnel tests in both two- and three-dimensional flow are presented but no correlation nor resume of the data has been included" (p. 1).
Date:
January 1944
Creator:
Rogallo, F. M.
Object Type:
Report
System:
The UNT Digital Library
General resistance tests on flying-boat hull models
Report re-examining known procedures for handling general resistance testing on flying-boat hull models, with particular attention paid to saving test time and improving the usefulness of the results to designers. While specific testing will likely always be needed, the procedures given in the report for condensing resistance data should make data analysis easier to apply to design.
Date:
February 1944
Creator:
Locke, F. W. S., Jr.
Object Type:
Report
System:
The UNT Digital Library
An investigation of aircraft heaters 14: an air and heat flow analysis of a ram-operated heater and duct system
Report presenting a method of graphical analysis that allows for the prediction of the thermal and aerodynamic performance of a ram-operated heater and duct system, for cabin heating or wing de-icing, at any altitude and airplane speed. Performance can be predicted from the isothermal total pressure drop across the components of the duct system at several ventilating air rates and the thermal output of the heater at various air and exhaust gas rates.
Date:
March 1944
Creator:
Boelter, L. M. K.; Morrin, E. H.; Martinelli, R. C. & Poppendiek, H. F.
Object Type:
Report
System:
The UNT Digital Library
An investigation of aircraft heaters 24: the heat meter in the transient state for unidirectional heat transfer
Report describing the behavior of the heat meter when it is used in thermal circuits which are under the influence of transient potentials. Three scenarios are considered: a heat meter suddenly placed on a hot surface, a heat meter mounted on the interior surface of the cabin wall of an uninsulated airplane climbing through air of decreasing temperature, and a heat meter mounted on the interior surface of the composite cabin wall of an airplane climbing through air of decreasing temperature.
Date:
September 1944
Creator:
Boelter, L. M. K.; Poppendiek, H. F.; Dunkle, R. V. & Gier, J. T.
Object Type:
Report
System:
The UNT Digital Library
An investigation of aircraft heaters 15: the emissivity of several materials
Report presenting a determination of the mean effective emissivity as a function of temperature for the surfaces of several metals and insulating materials. A description and discussion of the measuring technique is presented. The results are plotted on a variety of graphs.
Date:
January 1944
Creator:
Boelter, L. M. K.; Bromberg, R. & Gier, J. T.
Object Type:
Report
System:
The UNT Digital Library