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 Decade: 1940-1949
 Year: 1943
 Month: February
 Collection: National Advisory Committee for Aeronautics Collection
The belt method for measuring pressure distribution

The belt method for measuring pressure distribution

Date: February 1, 1943
Creator: Corson, Blake W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of thermal ice-prevention equipment for the B-24D airplane

Development of thermal ice-prevention equipment for the B-24D airplane

Date: February 1, 1943
Creator: Rodert, Lewis A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of angle of dead rise and angle of afterbody keel on the resistance of a model of a flying-boat hull

The effects of angle of dead rise and angle of afterbody keel on the resistance of a model of a flying-boat hull

Date: February 1, 1943
Creator: Willis, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flutter tests on SB2U model in 16-foot tunnel

Flutter tests on SB2U model in 16-foot tunnel

Date: February 1, 1943
Creator: Smith, N H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Generalized performance selection charts for single-engine pursuit airplanes

Generalized performance selection charts for single-engine pursuit airplanes

Date: February 1, 1943
Creator: Brevoort, Maurice J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed wind-tunnel tests of a 1/14-scale model of a four-engine cargo airplane

High-speed wind-tunnel tests of a 1/14-scale model of a four-engine cargo airplane

Date: February 2, 1943
Creator: Hamilton, William T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A hot-wire circuit with very small time lag

A hot-wire circuit with very small time lag

Date: February 1, 1943
Creator: Weske, John R
Description: A circuit for a hot-wire anemometer for the measurement of fluctuating flow is presented in the present report. The principal elements of the circuit are a Wheatstone bridge, one branch of which is the hot wire; and an electronic amplifier and a current regulator for the brief current which in combination maintain the bridge balance constant. Hence the hot wire is kept at practically constant resistance and temperature, and the time lag caused by thermal inertia of the wire is thereby reduced. Through the addition of a nonlinear amplifying stage the reading of the instrument has been rendered proportional to the velocity. A discussion of certain characteristics of the circuit and the results of related calibrating tests are given.
Contributing Partner: UNT Libraries Government Documents Department
Jet-boundary corrections to a yawed model in a closed rectangular wind tunnel

Jet-boundary corrections to a yawed model in a closed rectangular wind tunnel

Date: February 1, 1943
Creator: Swanson, Robert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Methods of Measurement of High Air Velocities by the Hot-Wire Method

Methods of Measurement of High Air Velocities by the Hot-Wire Method

Date: February 1, 1943
Creator: Weske, John R.
Description: Investigations of strengths of hot wires at high velocities were conducted with platinum, nickel, and tungsten at approximately 200 Degrees Celcius hot-wire temperature. The results appear to disqualify platinum for velocities approaching the sonic range; whereas nickel withstands sound velocity, and tungsten may be used for supersonic velocities under standard atmospheric conditions. Hot wires must be supported by rigid prolongs at high velocities to avoid wire breakage. Resting current measurements for constant temperature show agreement with King's relation.
Contributing Partner: UNT Libraries Government Documents Department
NACA Radio Ground-Speed System for Aircraft

NACA Radio Ground-Speed System for Aircraft

Date: February 1, 1943
Creator: Hastings, Charles E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Radio Ground-Speed System for Aircraft, Special Report

NACA Radio Ground-Speed System for Aircraft, Special Report

Date: February 1, 1943
Creator: Hastings, Charles E.
Description: A method that utilizes the Doppler effect on radio signals for determining the speed of an airplane and the distance traveled by the airplane has been developed and found to operate satisfactorily. In this method, called the NACA radio ground-speed system, standard readily available radio equipment is used almost exclusively and extreme frequency stability of the transmitters is not necessary. No complicated equipment need be carried in the airplane, as the standard radio transmitter is usually adequate. Actual flight tests were made in which the method was used and the results were consistent with calibrated air speed indications and stop-watch measurements. Inasmuch as the fundamental accuracy of the radio method is far better than either of the checking systems used, no check was made on the limitations of the accuracy.
Contributing Partner: UNT Libraries Government Documents Department
Piezoelectric Instruments of High Natural Frequency Vibration Characteristics and Protection Against Interference by Mass Forces

Piezoelectric Instruments of High Natural Frequency Vibration Characteristics and Protection Against Interference by Mass Forces

Date: February 1, 1943
Creator: Gohlka, Werner
Description: The exploration of the processes accompanying engine combustion demands quick-responding pressure-recording instruments, among which the piezoelectric type has found widespread use because of its especially propitious properties as vibration-recording instruments for high frequencies. Lacking appropriate test methods, the potential errors of piezoelectric recorders in dynamic measurements could only be estimated up to now. In the present report a test method is described by means of which the resonance curves of the piezoelectric pickup can be determined; hence an instrumental appraisal of the vibration characteristics of piezoelectric recorders is obtainable.
Contributing Partner: UNT Libraries Government Documents Department
A portable calibrator for dynamic strain gages

A portable calibrator for dynamic strain gages

Date: February 1, 1943
Creator: Mcpherson, Albert E
Description: A portable device for calibrating dynamic strain gages is described. The device contains a motor-driven cam, which applies alternating tensile loads to a metal strip 5/8 inch wide and 6 1/4 inches long. The cam is designed to produce a nearly sinusoidal variation of strain with time. Dynamic strain gages with gage lengths up to 5 inches may be calibrated by mounting them on the strip and by changing the frequency and the amplitude of the tensile load. The frequency may be varied from 15 to 30 cycles per second and the strain amplitude from 0 to 10x10-4 in steps of 2x10-4.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report

Date: February 1, 1943
Creator: Stack, John; Fedziuk, Henry A. & Cleary, Harold E.
Description: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
Contributing Partner: UNT Libraries Government Documents Department
Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

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

Date: February 1, 1943
Creator: Delano, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure loss in ducts with compound elbows

Pressure loss in ducts with compound elbows

Date: February 1943
Creator: Weske, John R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Progress report on fatigue of spot-welded aluminum

Progress report on fatigue of spot-welded aluminum

Date: February 1, 1943
Creator: Jackson, L. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The reduction of nonuseful pressure losses on air-cooled engine cylinders by means of improved finning and baffling

The reduction of nonuseful pressure losses on air-cooled engine cylinders by means of improved finning and baffling

Date: February 1, 1943
Creator: Wood, George P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Small-orifice tubes for minimizing dilution in exhaust-gas samples

Small-orifice tubes for minimizing dilution in exhaust-gas samples

Date: February 1, 1943
Creator: Olson, Walter T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tail Buffeting

Tail Buffeting

Date: February 1, 1943
Creator: Abdrashitov, G.
Description: An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing

Date: February 1, 1943
Creator: Toll, Thomas A.
Description: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of single and dual-rotating tractor propellers at low blade angles and of two-and three-blade tractor propellers at blade angles up to 65 degrees

Wind-tunnel tests of single and dual-rotating tractor propellers at low blade angles and of two-and three-blade tractor propellers at blade angles up to 65 degrees

Date: February 1, 1943
Creator: Gray, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department