National Advisory Committee for Aeronautics (NACA) - 1,263 Matching Results

Search Results

prev Results: 73 - 96 next
open access

Maximum Rates of Control Motion Obtained From Ground Tests

Description: 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 forc… more
Date: May 1944
Creator: Beeler, De E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of Dive-Recovery Flaps on an XP-51 Airplane

Description: Report presenting a flight investigation made to determine the effectiveness of dive-recovery flaps installed on the XP-51 airplane as a safety device for recovery from contemplated terminal-velocity dives. The flap installation is described and results are presented of measurements obtained during stick-free pull-ups and pull-outs made by deflecting the dive-recovery flaps to two selected values of flap angle .
Date: May 1945
Creator: Beeler, De E. & Williams, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Continuous Use of Internal Cooling to Suppress Knock in Aircraft Engines Cruising at High Power

Description: Report presenting an investigation of the possibility of using internal cooling instead of fuel enrichment to suppress knock and to estimate the fuel savings that will result. Data from four different sources was examined and an analysis of the fuel consumption was conducted. Four different types of coolants were explored.
Date: August 1944
Creator: Bell, Arthur H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Solidity, Blade Section, and Contravane Angle on the Characteristics of an Axial-Flow Fan

Description: Report presenting an axial flow fan tested with 5, 9, 12, 18, and 24 blades and with two different blade sections. The range of contravane angle and blade angle without contravanes was extended past results published for the same fan previously.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of the Characteristics of Air Scoops on a Fuselage

Description: Report presenting an investigation of the characteristics of air scoops in the NACA propeller-research tunnel. The investigation showed that, at inlet-velocity ratios equal to or greater than 0.3, scoops in a forward position on the fuselage gave total pressures in the inlet nearly equal to free-stream total pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Test of a Dual-Rotation Axial-Flow Fan

Description: Report presenting a dual-rotation axial-flow fan composed of two oppositely rotating 24-blade rotors. The fan was tested with various combinations of front and rear blade angles and with two combinations of front and rear solidities. For quantity coefficients above 0.3 the greatest pressure rise was obtained from 24 blades in each rotor with the blades adjusted to absorb equal torque at maximum pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank tests of a 1/8-size dynamic model of the PB2Y-3 airplane with increased power: NACA model 131

Description: Report presenting a study of the installation of 1800-horsepower engines in the PB2Y-3 airplane in place of the current 1200-horsepower engines. Stability and spray tests were made to determine the performance of the model on the water when tested at both the present and projected conditions of gross load and engine power. Results regarding aerodynamic tests and hydrodynamic tests are provided.
Date: June 1943
Creator: Bell, Joe W. & Havens, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank Tests of a 1/8-Size Dynamic Model of the PB2Y-3 Airplane with Simulated Jet Motors: NACA Models 131J, 131J-1 and 131J-2

Description: Report presenting an investigation to determine the effect of jet motors on the stability of the PB2Y-3 airplane at a gross load of 76,000 pounds. Results regarding Model 131J, Model 131J-1, and Model 131J-2 are provided.
Date: June 1943
Creator: Bell, Joe W. & Havens, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Angle of Dead Rise and Angle of Afterbody Keel on the Resistance of a Model of a Flying-Boat Hull

Description: Report presenting a series of models of flying-boat hulls tested to determine the effects of the angle of dead rise and the angle of afterbody keel on resistance and spray characteristics. Three angles of dead rise and three angles of afterbody keel were investigated. The results are expressed in nondimensional coefficients.
Date: February 1943
Creator: Bell, Joe W. & Willis, John M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Length-Beam Ration on Resistance and Spray of Three Models of Flying-Boat Hulls

Description: Report presenting an investigation of the effect of changes in the length-beam ratio of flying-boat hulls on resistance and spray. A family of three models of hulls of different length-beam ratios was used and, in order to maintain comparable hull sizes, the plan-form areas of the hulls were made approximately equal by keeping equal products of length and beam. Results regarding resistance, spray, and take-off performance are provided.
Date: October 1943
Creator: Bell, Joe W.; Garrison, Charlie C. & Zeck, Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The knock-limited performance of several miscellaneous fuels blended with a base fuel

Description: Report presenting investigations to determine the knock-limited performance of blends of 90 percent by volume AN-F-28, Amendment-2 fuel, and 10 percent by volume of the following fuels: tert-amyl alcohol, 2,6-dimethyl-1, 4-dioxane, methyl tert-butyl ether, methyl tert-butyl ketone, methyl isobutyl ketone, mesityl oxide, acetone, and diisopropyl ketone.
Date: July 1944
Creator: Bellman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-limited performance of several internal coolants

Description: Report presenting the effect of internal cooling on the knock-limited performance of AN-F-28 fuel in a CFR engine with the following internal coolants: water, methyl alcohol-water mixture, ammonia-methyl alcohol-water mixture, monomethyllamine-water mixture, dimethylamine-water mixture, and trimethylamine-water mixture.
Date: February 1944
Creator: Bellman, Donald R. & Evvard, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-limited power outputs from a CFR engine using internal coolants 1: monomethylamine and dimethylamine

Description: Report presenting an investigation to determine the knock-limited power obtainable by injecting water solutions of monomethylamine and dimethylamine as internal coolants into a CFR engine using AN-F-28, Amendment-2, fuel.
Date: December 1944
Creator: Bellman, Donald R.; Moeckel, W. E. & Evvard, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-limited power outputs from a CFR engine using internal coolants 2: six aliphatic amines

Description: Report presenting an investigation to determine the knock-limited performance of AN-F-28, Amendment-2, fuel in a DCFR engine when water solutions of the following aliphatic amines were added as internal coolants: monomethylamine, dimethylamine, ethylendiamine, diethylamine, triethylamine, and butylamine. Results regarding the mean effective pressure, indicated specific fuel competition, indicated specific liquid consumption, and knock-limited inlet-air pressure plotted against fuel-air ratio ar… more
Date: October 1945
Creator: Bellman, Donald R.; Moeckel, W. E. & Evvard, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Amphibious Floats on the Power-Off Stability and Control Characteristics of a Twin-Engine Cargo Airplane

Description: Report presenting power-off wind tunnel tests of a scale model of a twin-engine cargo airplane equipped with amphibious floats. Longitudinal and lateral stability and control characteristics were investigated for three flap positions.
Date: January 18, 1943
Creator: Belsley, Steven E. & Jackson, Roy P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Instrument for the Determination of Rain Densities in Flight

Description: Report presenting an investigation to develop an instrument for the determination of rain densities in this range in flight. The major requirements for the instrument are ease of operation, minimum weight and bulk, rapid response, and simplicity of installation.
Date: May 1943
Creator: Bemis, John R. & Houghton, Henry G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The influence of vertical-tail design and direction of propeller rotation on trim characteristics of a twin-engine-airplane model with one engine inoperative

Description: Report presenting testing to determine the influence of propeller rotation and vertical-tail design on the trim characteristics of a model of a twin-engine airplane with one engine inoperative. The tests showed that the effect of mode of propeller rotation on the directional trim characteristics of the model operating with asymmetric power was considerable. Results regarding the effect of mode of propeller rotation and effect of vertical-tail design are provided.
Date: February 1945
Creator: Bennett, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Early Detection of Cracks Resulting From Fatigue Stressing

Description: Report discusses an apparatus that may be used for indicating the formation of fatigue cracks or for following the progress of cracks. Details of the experiment and discussion of the way in which the deflection-crack area relationship may be used to monitor fatigue cracks are included.
Date: September 1944
Creator: Bennett, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Backflow Phenomenon in Centrifugal Superchargers

Description: Report presenting an investigation to determine the nature and extent of the reversal of flow, which occurs at the inlet of centrifugal superchargers over a considerable portion of the operating range. Results regarding lampback patterns, tuft studies, backflow surveys, and effect of impeller tip speed on backflow are provided.
Date: June 1945
Creator: Benser, William A. & Moses, Jason J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic-stability tests of a model of a flying boat and of a planing surface having a small downward projection (hook) on the planing bottom near the step

Description: Report presenting stability testing of two dynamic models in tank no. 1 in order to investigate the effects of adding a small projection, or hook, on the planing bottom of the forebody near the step of a seaplane. Tests with two different projections had a rather large effect on all of the trim limits and the landing stability.
Date: January 1943
Creator: Benson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Porpoising Characteristics of a Planing Surface Representing the Forebody of a Flying-Boat Hull

Description: Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
Date: May 1942
Creator: Benson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Bibliography and Review of Information Relating to the Hydrodynamics of Seaplanes

Description: Report presenting a bibliography and review of information related to the hydrodynamics of seaplanes. Characteristics of conventional hulls and floats are discussed to show the effects upon performance of changes in design parameters like dead rise, depth of step, and angle of afterbody keel. Other topics include floats, lateral stabilizers, aerodynamic and propulsive considerations, unconventional configurations, hydrofoils, and piloting and handling.
Date: September 1945
Creator: Benson, James M. & Bidwell, Jerold M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Landing Characteristics of a Model of a Flying Boat With the Depth of Step Reduced to Zero by Means of a Retractable Planing Flap

Description: "A model of a flying boat was tested to determine the landing characteristics when the depth of the step was reduced to zero by means of a retractable planing flap on the forebody" (p. 4). The results of stability and resistance testing are presented.
Date: February 1944
Creator: Benson, James M. & Freihofner, Anton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Methods and Charts for Computing Stability Derivatives of a V-Bottom Planing Surface

Description: Report presenting methods and charts for computing stability derivatives of a longitudinally straight V-bottom planing surface representing the forebody of a seaplane float or a flying-boat hull without chine flare. The charts for computing hydrodynamic derivatives were used in calculating the trim limit of stability for angles of dead rise of 10, 20, and 30 degrees.
Date: December 1943
Creator: Benson, James M. & Freihofner, Anton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen