Technical Report Archive & Image Library (TRAIL) - 39 Matching Results

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Notes on the technique of landing airplanes equipped with wing flaps

Description: "The proper landing of airplanes equipped with flaps, although probably no more difficult than landing without them, requires a different technique. The effects of flaps on the aerodynamics characteristics of a wing are given and, with the aid of figures and diagrams, a detailed comparison of the glide and landing of an airplane with and without flaps is made. The dangers attending improper execution and the importance of such factors as air speed fuselage attitude, glide-path angle, and contro… more
Date: January 1936
Creator: Gough, Melvin N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Performance of a DePalma Roots-Type Supercharger

Description: "The results of tests made to determine the performance of a DePalma-Roots supercharger are presented. The performance of the DePalma supercharger with atmospheric pressure at the discharge was compared with that of a hypothetical NACA Roots-type supercharger of the same displacement. The tests were conducted at speeds from 1,000 to 6,000 r.p.m. and at pressure differences from 0 to 15 inches of mercury" (p. 1).
Date: March 1936
Creator: Schey, Oscar W. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Air-Cooled Engine Cylinders Using Blower Cooling

Description: "An investigation was made to obtain information on the minimum quantity of air and power required to cool conventional air cooled cylinders at various operating conditions when using a blower. The results of these tests show that the minimum power required for satisfactory cooling with an overall blower efficiency of 100 percent varied from 2 to 6 percent of the engine power depending on the operating conditions. The shape of the jacket had a large effect on the cylinder temperatures. Increasi… more
Date: July 1936
Creator: Schey, Oscar W. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Piloting technique for recovery from spins

Description: "Systematic flight investigation of the spinning characteristics of various airplanes over a period of several years have given the pilots engaged in the testing a varied and extensive experience. From this experience certain general rules of procedure have been formulated, particularly for the sequence of operation of the controls in recovery from spins, and are recommended to the attention of all pilots" (p. 1).
Date: February 1936
Creator: McAvoy, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Procedure for determining speed and climbing performance of airships

Description: From Summary: "The procedure for obtaining air-speed and rate-of-climb measurements in performance tests of airships is described. Two methods of obtaining speed measurements, one by means of instruments in the airship and the other by flight over a measured ground course, are explained. Instruments, their calibrations, necessary correction factors, observations, and calculations are detailed for each method, and also for the rate-of-climb tests. A method of correction for the effect on density… more
Date: April 1936
Creator: Thompson, F. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The reduction of aileron operating force by differential linkage

Description: "It is shown that the control force of ordinary ailerons may be reduced to zero over a range of deflections and at a given flight condition by the use of an appropriate differential movement. Approximations to the ideal motion obtainable with a simple linkage are discussed and a chart that enables the selection of an appropriate crank arrangement is presented. Various aspects of the practical application of the system are discussed and it is concluded that a small fixed tab, deflected to trim b… more
Date: December 1936
Creator: Jones, Robert T. & Nerken, Albert I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Remarks on the Elastic Axis of Shell Wings

Description: The definitions of flexural center, torsional center, elastic center, and elastic axis are discussed. The calculation of elastic centers is dealt with in principle and a suggestion is made for the design of shear webs.
Date: April 1936
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of autogiro rotor-blade oscillations in the plane of the rotor disk

Description: An analysis of the factors governing the oscillation of an autogiro rotor blade in the plane of the rotor disk showed that the contribution of the air forces to the resultant motion was small and that the oscillation is essentially a direct effect of the rotor-blade flapping motion. A comparison of calculated oscillations with those measured in flight on three different rotors disclosed that the calculations gave satisfactory agreement with experiment. The calculated air forces on the rotor bla… more
Date: September 1936
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Tests of a Model of the NC Flying-Boat Hull - N.A.C.A. Model 44

Description: "A 1/7.06 full-size model of the NC-type hull was tested in the N.A.C.A. tank by both the general method and the specific or free-to-trim method. The results of the tests are given in curves plotted as non dimensional coefficients and are compared with the test results of N.A.C.A. model 11-A. The NC model (N.A.C.A. model 44) shows higher resistance than model 11-A at hump speed but lower resistance at high speeds. Model 44 has a higher best trim angle at the jump and a lower maximum positive tr… more
Date: May 1936
Creator: Bell, Joe W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank tests of models of floats for single-float seaplanes - First series

Description: "Large models of the Mark V and Mark VI floats used for single float seaplanes (National Advisory Committee for Aeronautics (NACA) models 41-A and 41-B, respectively) were tested in the NACA tank to provide general test data for typical single floats and a basis for possible improvements of their form. The resistance of model 41-B was greater than that of model 41-A, either when free to trim or at the best trim angle for each. The resistance of model 35-B (a pointed step hull tested free to tri… more
Date: April 1936
Creator: Parkinson, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank tests of models of flying boat hulls having longitudinal steps

Description: Four models with longitudinal steps on the forebody were developed by modification of a model of a conventional hull and were tested in the National Advisory Committee for Aeronautics (NACA) tank. Models with longitudinal steps were found to have smaller resistance at high speed and greater resistance at low speed than the parent model that had the same afterbody but a conventional V-section forebody. The models with a single longitudinal step had better performance at hump speed and as low hig… more
Date: July 1936
Creator: Allison, John M. & Ward, Kenneth E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise - NACA model 35 series

Description: From Summary: "The results of tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise are given in charts and are compared with results from tests of more conventional hulls. Increasing the angle of dead rise from 15 to 25 degrees: had little effect on the hump resistance; increased the resistance throughout the planning range; increased the best trim angle; reduced the maximum positive trimming moment required to obtain best trim angle; and h… more
Date: January 1936
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tanks test of a model of the hull of the Navy PB-1 flying boat - N.A.C.A. Model 52

Description: A model of the hull of the Navy PB-1 flying boat was tested in the N.A.C.A. tank as part of a program intended to provide information regarding the water performance of hulls of flying boats of earlier design for which hydrodynamic data have heretofore been unavailable. Tests were made according to the general method over the range of practical loadings with the model both fixed in trim and free to trim. A free-to-trim test according to the specific method was also made for the design load and … more
Date: August 1936
Creator: Allison, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of N.A.C.A. airfoils in the variable-density wind tunnel. Series 230

Description: The results of tests of six airfoils having the N.A.C.A. 230 mean line and varying in thickness from 0.06c to 0.21c are presented. These results agree with previous findings in showing that aerodynamically the best section is one of moderate thickness. The data are of value mainly in connection with the design of tapered wings having sections based on the N.A.C.A. 230 mean line.
Date: May 1936
Creator: Jacobs, Eastman N. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of Wing Flaps Suitable for Direct Control of Glide-Path Angle

Description: "Preliminary tests have been made for the purpose of obtaining a flap arrangement suitable for direct and immediate control of the steepness of the glide path of an airplane, a use for which present flaps are not satisfactory. An attempt has been made to develop a flap giving a reasonably high maximum lift coefficient with relatively low deflection and maintaining this value of the maximum lift coefficient with a large increase of deflection, the increase in deflection being accompanied by a la… more
Date: January 1936
Creator: Weick, Fred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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