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An Approximate Method of Calculation of Relative Humidity Required to Prevent Frosting on Inside of Aircraft Pressure Cabin Windows, Special Report

Description: This report has been prepare in response to a request for information from an aircraft company. A typical example was selected for the presentation of an approximate method of calculation of the relative humidity required to prevent frosting on the inside of a plastic window in a pressure type cabin on a high speed airplane. The results of the study are reviewed.
Date: December 5, 1940
Creator: Jones, Alun R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Full-Scale Wind-Tunnel Investigation of Wing Ducts for Radiators, Special Report

Description: "Wing ducts for liquid-cooled engine radiators have been investigated in the N.A.C.A. full-scale wind tunnel on a large model airplane. The tests were made to determine the relative merits of several types of duct and radiator installations for an airplane of a particular design. In the test program the principal duct dimensions were systematically varied, and the results are therefore somewhat applicable to the general problems of wing duct design, although they should be considered as prelimi… more
Date: March 1938
Creator: Silverstein, Abe & Nickle, F. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing

Description: "An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of several scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and havin… more
Date: September 1939
Creator: McHugh, James G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

Description: "The pressure distribution on the fuselage of a midwing airplane model was measured in the NACA 8-foot high speed wind tunnel at speeds from 140 to 440 miles per hour for lift coefficients ranging from -0.2 to 1.0. The primary purpose of the tests was to provide data showing the air pressures on various parts of the fuselage for use in structural design. The data may also be used for the design of scoops and vents. The results show that the highest negative pressures occurred near the wing and … more
Date: November 1939
Creator: Delano, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Prevention of Ice on the Airplane Windshield

Description: "An investigation has been completed on several methods for the prevention and removal of ice on an airplane windshield. Tests were made on the use of electric heating, hot-air heating, and an alcohol-dispensing, rotating wiper blade. The results showed that vision through the airplane windshield could be maintained during severe icing conditions by the use of heat" (p. 1).
Date: November 1939
Creator: Rodert, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Tests in the NACA Tank to Investigate the Fundamental Characteristics of Hydrofoils

Description: Report discusses an investigation into the hydrodynamic properties and general behavior of simple hydrofoils. The experimental results are presented as curves of the lift and drag coefficients plotted against speed for angles of attack and depths. Properly designed hydrofoil sections were determined to have excellent characteristics and a significant reduction in the speed of cavitation.
Date: September 1940
Creator: Ward, Kenneth E. & Land, Norman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tandem Air Propellers

Description: Report discussing tests of 2-blade, adjustable-pitch, counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency. The characteristics at several pitch settings and diameter spacings were compared with 2-blade and 4-blade propellers. Tandem propellers were found to have an advantage over single propellers at higher pitch settings.
Date: August 1937
Creator: Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of Exhaust-Heat De-Icing, Special Report

Description: The National Advisory Committee for Aeronautics has conducted exhaust-heat de-icing tests inflight to provide data needed in the application of this method of ice prevention. The capacity to extract heat from the exhaust gas for de-icing purposes, the quantity of heat required, and other factors were examined. The results indicate that a wing-heating system employing a spanwise exhaust tube within the leading edge of the wing will make available for de-icing purposes between 30 and 35 percent o… more
Date: September 1940
Creator: Rodert, Lewis A. & Jones, Alun R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of Exhaust Gas Jet Propulsion, Special Report

Description: "Flight tests were conducted on the XP-41 airplane, equipped with a Pratt & Whitney R1830-19, 14-cylinder, air-cooled engine, to determine the increase in flight speed obtainable by the use of individual exhaust stacks directed rearwardly to obtain exhaust-gas thrust. Speed increases up to 18 miles per hour at 20,000 feet altitude were obtained using stacks having an exit area of 3.42 square inches for each cylinder. A slight increase in engine power and decrease in cylinder temperature at a gi… more
Date: November 1940
Creator: Pinkel, Benjamin & Turner, L. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model, Special Report

Description: Report discusses the important principles involved in the operation of a baffle for an engine cylinder and how using a correctly designed baffle can improve cooling. The baffle-exit radius and width and exit-duct length were found to be the most important parts of the baffle and a baffle that gave a relatively uniform temperature distribution was designed.
Date: April 1937
Creator: Brevoort, Maurice J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability of Castering Wheels for Aircraft Landing Gears, Special Report

Description: In many installations of castering rubber-tired wheels there is a tendency for the wheel to oscillate violently about the spindle axis. This phenomenon, popularly called 'shimmy,' has occurred in some airplane tail wheels and has been corrected in two ways: first by the application of friction in the spindles of the tail wheels; and, second, by locking the wheels while taxiing at high speeds. Shimmy is common with the large wheels used as nose wheels in tricycle landing gears and, since it is i… more
Date: September 1937
Creator: Kantrowitz, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Drag and Propulsive Characteristics of Air-Cooled Engine-Nacelle Installations for Large Airplanes, Special Report

Description: "An investigation is in progress in the NACA full-scale wind tunnel to determine the drag and propulsive efficiency of nacelle sizes. In contrast with the usual tests with a single nacelle, these tests were conducted with nacelle-propeller installations on a large model of a 4-engine airplane. Data are presented on the first part of the investigation, covering seven nacelle arrangements with nacelle diameters from 0.53 to 1.5 times the wing thickness" (p. 1).
Date: August 1939
Creator: Silverstein, Abe & Wilson, Herbert A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Surface Irregularities on Wing Drag 1 - Rivets and Spot Welds

Description: "Tests have been conducted in the NACA 8-foot high-speed wind tunnel to determine the effect of exposed rivet heads and spot welds on wing drag. Most of the tests were made with an airfoil of 5-foot chord. The air speed was varied from 80 to 500 miles per hour and the lift coefficient from 0 to 0.30" (p. 1).
Date: February 1938
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Surface Irregularities on Wing Drag 4 - Manufacturing Irregularities

Description: "Tests were made in the NACA 8-foot high speed wind tunnel of a metal-covered, riveted, 'service' wing of average workmanship to determine the aerodynamic effects of the manufacturing irregularities incident to shop fabrication. The wing was of 5-foot chord and of NACA 23012 section and was tested in the low-lift range at speeds from 90 to 450 miles per hour corresponding to Reynolds numbers from 4,000,000 to 18,000,000. At a cruising condition the drag of the service wing was 46% higher than t… more
Date: February 1938
Creator: Robinson, Russell G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Surface Irregularities on Wing Drag 2 - Lap Joints

Description: Tests have been made in the NACA 8-foot high-speed wind tunnel of the drag caused by four types of lap joint. The tests were made on an airfoil of NACA 23012 section and 5-foot chord and covered in a range of speeds from 80 to 500 miles per hour and lift coefficients from 0 to 0.30. The increases in profile drag caused by representative arrangements of laps varied from 4 to 9%. When there were protruding rivet heads on the surface, the addition of laps increased the drag only slightly. Laps on … more
Date: February 1938
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Large-Scale Boundary-Layer Control Tests on Two Wings in the NACA 20-Foot Wind Tunnel, Special Report

Description: Report discussing tests performed on two different wings to determine the increase in lift obtainable by removing the boundary layer and power required for the blower. The results for the stub wing were more favorable than the large-span wing.
Date: April 1935
Creator: Freeman, Hugh B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report

Description: At the request of the Materiel Division of the Army Air Corps, seven tapered wings having sections based on the N.A,C.A. 230 mean line were tested in the variable-density wind tunnel, The characteristics of the wings are given.
Date: August 1937
Creator: Anderson, Raymond F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Surface Irregularities on Wing Drag 3 - Roughness

Description: "Tests have been made in the N.A.C.A. 8-foot high-speed wind tunnel of the drag caused by roughness on the surface of an airfoil of N.A.C.A. 23012 section and 5-foot chord. The tests were made at speeds from 80 to 500 miles per hour at lift coefficients from 0 to 0.30. For conditions corresponding to high-speed flight, the increase in the drag was 30 percent of the profile drag of the smooth airfoil for the roughness produced by spray painting and 63 percent for the roughness produced. by 0.003… more
Date: February 1938
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

Description: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It is shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients.
Date: January 1943
Creator: Allen, H. Julian & Nitzberg, Gerald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Airfoils Designed to Delay the Compressibility Burble

Description: "Development of airfoil sections suitable for high-speed applications has generally been difficult because little was known of the flow phenomenon that occurs at high speeds. A definite critical speed has been found at which serious detrimental flow changes occur that lead to serious losses in lift and large increases in drag. This flow phenomenon, called the compressibility burble, was originally a propeller problem, but with the development of higher speed aircraft serious consideration must … more
Date: June 1939
Creator: Stack, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Three Exit-Area Control Devices on an N.A.C.A. Cowling, Special Report

Description: "Adjustable cowling flaps, an adjustable-length cowling skirt, and a bottom opening with adjustable flap were tested as means of controlling the rate of cooling-air flow through an air-cooled radial-engine cowling. The devices were tested in the NACA 20-foot tunnel on a model wing-nacelle-propeller combination, through an airspeed range of 20 to 80 miles per hour, and with the propeller blade angle set 23 degrees at 0.75 of the tip radius. The resistance of the engine to air flow through the co… more
Date: May 1940
Creator: McHugh, James G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Resume of Present Data on Load Distribution on Slots and Flaps, Special Report

Description: This report covers a study of the generally available data on load distribution on slots and flaps. The study was made by the National Advisory Committee for Aeronautics at the request of the Material Division, Army Air Corps to furnish information applicable to design criteria for slots and flaps of various types. The data are presented in three main sections: slots (Handley page type), auxiliary airfoils (fixed), and flaps.
Date: April 1934
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Lift Characteristics of an NACA 27-212 Airfoil Equipped With Two Types of Flap, Special Report

Description: "An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 airfoil with a 20% chord split flap and with two arrangements of a 25.66% chord slotted flap to determine the section lift characteristics as affected by flap deflection for the split flap and as affected by flap deflection, flap position, and slot shape for the slotted flap. For the two arrangements of the slotted flap, the flap positions for maximum section lift are given. Comparable data on the… more
Date: September 1940
Creator: Swanson, Robert S. & Schuldenfrei, Marvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Model Tests of a Wing-Duct Cooling System for Radial Engines, Special Report

Description: "Wind-tunnel tests were conducted on a model wing-nacelle combination to determine the practicability of cooling radial engines by forcing the cooling air into wing-duct entrances located in the propeller slipstream, passing the air through the engine baffles from rear to front, and ejecting the air through an annular slot near the front of the nacelle. The drag of the cowlings tested was definitely less than for the conventional N.A.C.A. cowling, and the pressure available at low air speed cor… more
Date: February 1939
Creator: Biermann, David & Valentine, E. Floyd
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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