1,263 Matching Results

Search Results

prev Results: 73 - 96 next
open access

Critical Speeds and Profile Drag of the Inboard Sections of a Conventional Propeller

Description: Report presenting the section critical speeds and profile drags of the shank and hub sections of a propeller used on a current liquid-cooled-engine pursuit type of airplane. Results indicated that serious adverse compressibility effects can be expected at speeds of about 400 miles per hour. Suitable fairings for shank and hub sections were found to be necessary for maximum propulsive efficiency.
Date: September 1941
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department
open access

Dynamic stress calculations for two airplanes in various gusts

Description: Report presenting a series of calculations made to determine the probable dynamic wing stress of two large airplanes in atmospheric gusts. The results indicate that in both isolated and repeated gusts of probable occurrence, the dynamic overstress is about 10 percent when referred to the present static design standard.
Date: September 1941
Creator: Pierce, Harold B.
Partner: UNT Libraries Government Documents Department
open access

Tests of Bell XP-63 Low-Drag Wing Model With Split Flap

Description: Report presenting tests on the Bell XP-63 wing root section fitted with an 0.18c split flap hinged at approximately 0.805c on the lower surface. The tests were conducted to determine the effect of a 10 degree deflection of the split flap on the drag characteristics of the model at low lift coefficients.
Date: September 1941
Creator: Underwood, W. J.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 4: A Medium Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil

Description: Report presenting tests made in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a medium amount of aerodynamic overhanging balance. In this investigation, the effects of the shape of the flap-nose overhang and the gap at the nose of the flap have been determined. The results indicate that, generally, the lift effectiveness of the aerodynamically balanced flap was increased slightly over that of a plain flap when a blunt or medium flap nose was use… more
Date: September 1941
Creator: Ames, Milton B., Jr. & Eastman, Donald R., Jr.
Partner: UNT Libraries Government Documents Department
open access

Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps

Description: "Additional tests as recommended in reference 1 were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane to determine the angle of attack of horizontal tail and the elevator angles required for trim with flaps down" (p. 1).
Date: October 1941
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Factors Affecting the Ability of a Pilot to Return an Airplane to Level From a Banked Attitude by Use of the Rudder Alone and Without Change of Heading

Description: Report presenting a study of the aerodynamic factors upon which the ability to perform the maneuver depends in an attempt to obtain a better understanding of the conditions involved and, if possible, to evolve criterions that may be used during design.
Date: October 1941
Creator: Harmon, S. M.
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

The effects of hub drag, solidity, dual rotation, and number of blades upon the efficiency of high-pitch propellers

Description: Report presenting an investigation of the effects of hub drag, solidity, dual rotation, and number of blades on the efficiency of high-pitch propellers. Testing occurred with two, three, four, and six-blade single propellers and four and six-blade dual-rotating propellers equipped with spinners and tested at a range of blade angles from 35 to 65 degrees. Results regarding a comparison of the large and small spinners, effects of spinners, comparison of constant-speed propellers, characteristics … more
Date: October 1941
Creator: Reid, Elliott G.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Wing-Gun Fairings on a Fighter Type Airplane

Description: Description is given of flight tests conducted on gun fairings, designed to correct the detrimental effects of the projecting and submerged wing guns on an F4F-3 fighter. It was found that the installation of unfaired guns on a clean wing resulted in a premature stall that increased the stalling speed in the carrier-approach and landing conditions of flight by suitably fairing the guns, it was possible to reduce the stalling speeds to values approaching very nearly the clean-wing values.
Date: October 1941
Creator: Nissen, J. M. & White, M. D.
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

The Selection of Propellers for High Thrust at Low Airspeed

Description: Problem of improving thrust at low speeds is primarily one of reducing angle of attack of operation of sections to improve L/D or reducing blade helix angle. An analysis, based on recent propeller data, is presented for determining improvements in thrust or efficiency which could be obtained by increased number of blades, increased blade width, increased diameter, dual rotation, and two-speed gearing. All methods were found very effective, particularly two-speed gearing.
Date: October 1941
Creator: Biermann, David & Conway, Robert N.
Partner: UNT Libraries Government Documents Department
open access

A study of the effects of vertical tail area and dihedral on the lateral maneuverability of an airplane

Description: Report presenting a theoretical investigation of the influence of changes in vertical tail area and dihedral angle on the lateral flying characteristics of an airplane. Lateral motions were computed for nine different combinations of vertical tail area and dihedral. Results regarding the lateral motions due to applied rolling moment with different amounts of accompanying pawing moment and lateral motions due to applied yawing moment are provided.
Date: October 1941
Creator: Fehlner, Leo F.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of an NACA 23012 airfoil with an 18.05 percent chord Maxwell slat and with trailing-edge flaps

Description: Report presenting an investigation in the 7- by 10-foot wind tunnel of an NACA 23012 airfoil with an 18.05-percent-chord Maxwell leading-edge slat and with a slotted and a split flap. The main purpose of the investigation was to determine the optimum slot gap of the Maxwell slat for, and the aerodynamic section characteristics of, the airfoil with several deflections of both types of flap.
Date: October 1941
Creator: McKee, John W.
Partner: UNT Libraries Government Documents Department
open access

Effect of Humidity on Several Supercharger Parameters

Description: Report presenting testing to determine if the change of several specific variables with extreme change of humidity and test-bench temperature will have an appreciable effect on several parameters used to determine supercharger performance.
Date: November 1941
Creator: Ellerbrock, Herman H., Jr. & Goldstein, Arthur W.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Elevator Deflections Used in Landings of Several Airplanes

Description: "A collection of data on the elevator deflections used in landings of several airplanes is presented in tabular form. The physical characteristics of these airplanes are also given. The elevator deflections used in landing some airplanes was found to be as much as 14.4 degrees greater than that used to stall under the same flight and loading conditions" (p. 1).
Date: November 1941
Creator: Vensel, Joseph R.
Partner: UNT Libraries Government Documents Department
open access

Investigation of performance of 9-cylinder engine using large valve overlap and eclipse fuel-injection system

Description: Report presenting single-cylinder tests were made with several different engines over a period of time, which have shown that a large overlap between the time of inlet valve opening and exhaust valve closing results in a considerable increase in the maximum power obtainable from a supercharged engine and reduces cylinder temperatures.
Date: November 1941
Creator: Young, Alfred W.
Partner: UNT Libraries Government Documents Department
open access

Tests of a 0.1475c Aileron With a Tab on Low-Drag Section for Curtiss XP-60 Airplane in the Low-Turbulence Tunnel

Description: "Preliminary two-dimensional tests of the hinge-moment characteristics of a 0.1725c internally balanced aileron on the subject XP-60 wing section indicated that more internal balance would be required if light stick forces were to be obtained at high speeds. The present series of tests were therefore undertaken in order to investigate methods of reducing the slope of the hinge-moment curve while still maintaining the required aileron effectiveness" (p. 1).
Date: November 1941
Creator: von Doenhoff, A. E. & Underwood, W. J.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Development of a Plug-Type Spoiler-Slot Aileron for a Wing With a Full-Span Slotted Flap and a Discussion of Its Application

Description: Report presenting an investigation in the NACA 7- by 10-foot wind tunnel of several arrangements of a plug-type, spoiler-slot aileron on an NACA 23012 airfoil with a full-span slotted flap. The results indicated that a plug-type, spoiler-slot aileron probably has negligible drag in the neutral position and will provide satisfactory lateral control for airplanes equipped with full-span slotted flaps.
Date: November 1941
Creator: Rogallo, Francis M. & Swanson, Robert S.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA 23012 Airfoil

Description: Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated th… more
Date: November 1941
Creator: Purser, Paul E. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of Eight-Blade Single and Dual-Rotating Propellers in the Tractor Position

Description: Tests of 10-ft. diameter, eight-blade, single - and dual - rotating propellers were conducted in 20-ft propeller research tunnel. Propellers were mounted at front end of a streamline body in spinners that covered hubs and parts of shanks. Effect of a symmetrical wing mounted in slipstream was investigated. Blade-angle settings ranged from 20 Degrees to 65 Degrees. Results indicated that dual rotation resulted in gains of from 1 to 8 percent in efficiency over single rotation for eight-blade pro… more
Date: November 1941
Creator: Biermann, David & Gray, W. H.
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

Internally Finned Honeycomb Radiators

Description: Report presenting the performance of several internally finned radiators and a comparison with more conventional honeycomb radiators. In a typical case, the new radiator can be designed with 55 percent less volume and 18 percent less power expenditure while dissipating the same amount of heat.
Date: December 1941
Creator: Tifford, Arthur N.
Partner: UNT Libraries Government Documents Department
open access

Lift and Drag Characteristics of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: Report presenting a wooden model equipped with a slotted flap that was tested in the two-dimensional tunnel. It represented a wing section of the Curtiss-Wright P-60A airplane and the NACA 66,2-118 section. Results regarding lift characteristics, drag coefficients, and flap deflection characteristics are provided.
Date: December 1941
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen