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 Decade: 1940-1949
 Serial/Series Title: NACA Technical Memorandums
 Collection: Technical Report Archive and Image Library
Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Date: November 1, 1942
Creator: Ackeret, J.
Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of rotating-wing aircraft with blade-pitch control

Aerodynamics of rotating-wing aircraft with blade-pitch control

Date: February 1, 1940
Creator: Pfluger, A
Description: In the present report, with the aid of the usual computation methods, a rotor is investigated the pitch of whose blades is capable of being controlled in such a manner that it varies linearly with the flapping angle. To test the effect of this linkage on the aircraft performance, the theory is applied to an illustrative example.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of the Fuselage

Aerodynamics of the Fuselage

Date: December 1, 1942
Creator: Multhopp, H.
Description: The present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something like a neutral stability point the position of which on oblong fuselages appears to be associated with the lift increase of the fuselage in proximity to the zero lift, according to the present experiments. The Pitching moments of the fuselage can be determined with comparatively great reliability so far as the flow conditions in the neighborhood of the axis of the fuselage can be approximated if the fuselage were absent, which, in general, is not very difficult. For the unstable contribution of the fuselage to the static longitudinal stability of the airplane it affords comparatively simple formulas, the evaluation of which offers little difficulty. On the engine nacelles there is, in addition a very substantial wing moment contribution induced ...
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Air transport by gliders : some technical observations

Air transport by gliders : some technical observations

Date: June 1, 1941
Creator: Stepniewski, Wieslaw
Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Date: June 1, 1949
Creator: Gothert, B
Description: Report is a brief summary of investigations on symmetrical and cambered airfoils in the DVL high-speed tunnel. Some information on the effects of low aspect ratio are also included.
Contributing Partner: UNT Libraries Government Documents Department
Airscrew Gyroscopic Moments

Airscrew Gyroscopic Moments

Date: September 1, 1946
Creator: Bock, G.
Description: When flying in a turn or pulling out of a dive, the airscrew exerts a gyroscopic moment on the aircraft, In the case of airscrews with three or more blades, arranged symmetrically, the value of the gyroscopic moment is J(sub x) omega(sub x) omega(sub y), where J(sub x) denotes the axial moment of inertia about the axis of rotation of the airscrew, omega(sub x) the angular upeed of the airscrew about its axis, and omega (sub Y) the rotary speed of the whole aircraft about an axis parallel to the plane of the airscrew (e.g., when pulling up, the transverse axis of the aircraft). The gyroscopic moment then tends to rotate the aircraft about an axis perpendicular to those of the two angular speeds and, in the came of airscrews with three or more blades, is constant during a revolution of the airscrew. With two-bladed airscrews, on the contrary, although the calculate gyroscopic moment represents the mean value in time, it fluctuates about this value with a frequency equal to twice the revolutions per minute. In addition, pulsating moments likewise occur about the other two axes. This fact is known from the theory of the asymmetrical gyro; the calculations that ...
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Analysis of Experimental Investigations of the Planing Process of the Surface of Water

Analysis of Experimental Investigations of the Planing Process of the Surface of Water

Date: March 1, 1944
Creator: Sottorf, W.
Description: Pressure distribution and spray measurements were carried out on rectangular flat and V-bottom planing surfaces. Lift, resistance, and center of pressure data are analyzed and it is shown how these values may be computed for the pure planing procees of a flat or V-bottom suface of arbitrary beam, load and speed, the method being illustrated with the aid of an example.
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Analytical theory of the Campini propulsion system

Analytical theory of the Campini propulsion system

Date: March 1, 1942
Creator: Campini, S
Description: Following the description of the new propulsion system and the definition of the propulsive efficiency, this efficiency is calculated under various conditions of flight with allowance for all internal losses. The efficiency and consumption curves are plotted, their practical values discussed and the behavior of the system analyzed at various altitudes and speeds. The immediate possibilities of the new system in flight at high and very high altitudes in relation to the theoretical and experimental results are discussed in detail.
Contributing Partner: UNT Libraries Government Documents Department
Analytical Treatment of Normal Condensation Shock

Analytical Treatment of Normal Condensation Shock

Date: July 1, 1947
Creator: Heybey
Description: The condensation of water vapor in an air consequences: acquisition of heat (liberated heat vaporization; loss of mass on the part of the flowing gas (water vapor is converted to liquid); change in the specific gas constants and of the ratio k of the specific heats (caused by change of gas composition). A discontinuous change of state is therefore connected with the condensation; schlieren photographs of supersonic flows in two-dimensional Laval nozzles show two intersecting oblique shock fronts that in the case of high humidities may merge near the point of intersection into one normal shock front.
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Application of the methods of gas dynamics to water flows with free surface I : flows with no energy dissipation

Application of the methods of gas dynamics to water flows with free surface I : flows with no energy dissipation

Date: March 1, 1940
Creator: Preiswerk, Ernst
Description: The application is treated in sufficient detail to facilitate as much as possible its application by the engineer who is less familiar with the subject. The present work was undertaken with two objects in view. In the first place, it is considered as a contribution to the water analogy of gas flows, and secondly, a large portion is devoted to the general theory of the two-dimensional supersonic flows.
Contributing Partner: UNT Libraries Government Documents Department
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