You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Serial/Series Title: NACA Technical Reports
 Collection: National Advisory Committee for Aeronautics Collection
Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil

Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark y airfoil

Date: January 1, 1933
Creator: Clay, William C & Theodorsen, Theodore
Description: This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both in the laboratory and in flight show conclusively that it is necessary to heat only the front portion of the wing surface to effect complete prevention. Experiments in flight show that a vapor-heating system which extracts heat from the exhaust and distributes it to the wings is an entirely practical and efficient method for preventing ice formation.
Contributing Partner: UNT Libraries Government Documents Department
The interference between struts in various combinations

The interference between struts in various combinations

Date: January 1, 1934
Creator: Biermann, David & Herrnstein, William H , Jr
Description: This report presents the results of wind tunnel tests made to determine the interference drag arising from various arrangements of streamline struts and round struts, or cylinders. Determinations were made of the interference drag of struts spaced side by side, struts in tandem, tandem struts encased in a single fairing, a strut intersecting a plane, and struts intersecting to form a v. Three sizes of struts were used for most of the tests. These tests show that the interference drag arising from struts in close proximity may be of considerable magnitude, in some instances amounting to more than the drag of the struts themselves.
Contributing Partner: UNT Libraries Government Documents Department
Negative thrust and torque characteristics of an adjustable-pitch metal propeller

Negative thrust and torque characteristics of an adjustable-pitch metal propeller

Date: January 1, 1934
Creator: Hartman, Edwin P
Description: This report presents the results of a series of negative thrust and torque measurements made with a 4 foot diameter model of a conventional aluminum-alloy propeller. The tests were made in the 20-foot propeller-research tunnel of the National Advisory Committee for Aeronautics. The results show that the negative thrust is considerably affected by the shape and size of the body behind the propeller, that the maximum negative thrust increases with decrease in blade-angle setting, and that the drag of a locked propeller may be greatly reduced by feathering it into the wind. Several examples of possible applications of the data are given.
Contributing Partner: UNT Libraries Government Documents Department
The NACA tank : a high-speed towing basin for testing models of seaplane floats

The NACA tank : a high-speed towing basin for testing models of seaplane floats

Date: January 1, 1934
Creator: Truscott, Starr
Description: This report describes the high-speed model towing basin of the National Advisory Committee for Aeronautics, usually referred to as the NACA Tank. The purpose of this piece of equipment is to enable the Committee to provide information and data regarding the performance of seaplanes on the water analogous to the information furnished concerning the performance of airplanes in the air.
Contributing Partner: UNT Libraries Government Documents Department
The NACA high-speed wind tunnel and tests of six propeller sections

The NACA high-speed wind tunnel and tests of six propeller sections

Date: January 1, 1934
Creator: Stack, John
Description: This report gives a description of the high-speed wind tunnel of the National Advisory Committee for Aeronautics. The operation of the tunnel is also described and the method of presenting the data is given. An account of an investigation of the aerodynamic properties of six propeller sections is included.
Contributing Partner: UNT Libraries Government Documents Department
Performance of a fuel-injection spark-ignition engine using a hydrogenated safety fuel

Performance of a fuel-injection spark-ignition engine using a hydrogenated safety fuel

Date: January 1, 1934
Creator: Schey, Oscar W & Young, Alfred W
Description: This report presents the performance of a single-cylinder test engine using a hydrogenated safety fuel. The safety fuel has a flash point of 125 degrees f. (Cleveland open-dup method), which is high enough to remove most of the fire hazard, and an octane number of 95, which permits higher compression ratios to be used than are permissible with most undoped gasolines.
Contributing Partner: UNT Libraries Government Documents Department
The experimental determination of the moments of inertia of airplanes

The experimental determination of the moments of inertia of airplanes

Date: January 1, 1934
Creator: Soule, Hartley A & Miller, Marvel P
Description: The application of the pendulum method to the experimental determination of the moments of inertia of airplanes is discussed in this report. Particular reference is made to the effects of the air, in which the airplane is immersed, on the swinging tests and to the procedure by which these effects are taken into account. This procedure has been used for some time, and the data on several airplanes for which the moments of inertia have been found are included.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests on combinations of a wing with fixed auxiliary airfoils having various chords and profiles

Wind-tunnel tests on combinations of a wing with fixed auxiliary airfoils having various chords and profiles

Date: January 1, 1934
Creator: Weick, Fred E & Sanders, Robert
Description: This report presents the results of wind tunnel tests on various auxiliary airfoils having three different airfoil sections and several different chord lengths in combination with a Clark y model wing in a sufficient number of relative positions to determine the optimum with regard to certain criterions of aerodynamic performance. The airfoil sections included a symmetrical profile, one of medium camber, and a highly cambered one. The chord sizes of the auxiliary airfoils ranged from 7.5 to 25 percent of the chord of the main wing, and the span was equal to that of the main wing.
Contributing Partner: UNT Libraries Government Documents Department
Increasing the air charge and scavenging the clearance volume of a compression-ignition engine

Increasing the air charge and scavenging the clearance volume of a compression-ignition engine

Date: January 1, 1934
Creator: Spanogle, J A; Hicks, C W & Foster, H H
Description: The object of the investigation presented in this report was to determine the effects of increasing the air charge and scavenging the clearance volume of a 4-stroke-cycle compression-ignition engine having a vertical-disk form combustion chamber. Boosting the inlet-air pressure with normal valve timing increased the indicated engine power in proportion to the additional air inducted and resulted in smoother engine operation with less combustion shock. Scavenging the clearance volume by using a valve overlap of 145 degrees and an inlet-air boost pressure of approximately 2 1/2 inches of mercury produced a net increase in performance for clear exhaust operation of 33 percent over that obtained with normal valve timing and the same boost pressure. The improved combustion characteristics result in lower specific fuel consumption, and a clearer exhaust.
Contributing Partner: UNT Libraries Government Documents Department
Determination of the theoretical pressure distribution for twenty airfoils

Determination of the theoretical pressure distribution for twenty airfoils

Date: January 1, 1934
Creator: Garrick, I E
Description: This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons with experiment are indicated. The results presented may be of value in predicting structural loads and also in a correlation of theoretical pressure gradients with profile resistance.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST