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On the Flow of a Compressible Fluid by the Hodography Method 2: Fundamental Set of Particular Flow Solutions of the Chaplygin Differential Equation
Report presenting the utilization of the differential equation of Chaplygin's jet problem to give a systematic development of particular solutions of the hodograph flow equations, which extends the treatment of Chaplygin into the supersonic range and completes the set of particular solutions. The solutions serve to place on a reasonable basis the use of velocity correction formulas for the comparison of incompressible and compressible flows.
Date:
November 1944
Creator:
Kaplan, Carl
System:
The UNT Digital Library
The Theory of Propellers 3: The Slipstream Contraction With Numerical Values for Two-Blade and Four-Blade Propeller
Report presenting the magnitude of slipstream contraction, which provides information about the conditions of the ultimate wake. Curves and tables are given for the contraction coefficient of two-blade and four-blade propellers for various values of the advance ratio; the contraction coefficient is defined as the contraction in the diameter of the wake helix in terms of the wake diameter at infinity.
Date:
November 1944
Creator:
Theodorsen, Theodore
System:
The UNT Digital Library
The Theory of Propellers 4: Thrust, Energy, and Efficiency Formulas for Single- and Dual-Rotating Propellers With Ideal Circulation Distribution
Report presenting simple and exact expressions for the efficiency of single- and dual-rotating propellers with ideal circulation distribution as given by Goldstein functions for single-rotating propellers and by the new functions for dual-rotating propellers from part I of this series. Efficiency is found to depend primarily on a defined load factor and on an axial loss factor. Tables and graphs are included for practical use of the results.
Date:
November 1944
Creator:
Theodorsen, Theodore
System:
The UNT Digital Library
Cascade investigation of buckets for a modern aircraft turbosupercharger
Report presenting a cascade investigation in two-dimensional flow in the 5-inch cascade tunnel and the 1-inch turbine-element testing apparatus to obtain a satisfactory bucket design for use in a modern aircraft turbosupercharger. Results regarding the root sections, pitch sections, and tip sections are provided.
Date:
November 1944
Creator:
Kantrowitz, Arthur & Erwin, John R.
System:
The UNT Digital Library
Experimental Study of the Coating Found on Scuffed Cast-Iron Piston Rings During Operation in Nitrided-Steel Cylinders
Report presenting cast-iron piston rings that were run in nitrided-steel cylinder barrels under scuffing conditions and showed a coating material on the scuffed areas. Only a few of the 14 etching reagents that were tried attacked the coating chemically, indicating good corrosion resistance. Results regarding the occurrence of coating, metallurgical characteristics, and chemical characteristics are provided.
Date:
November 1944
Creator:
Kittel, J. Howard & Vierthaler, Walter A.
System:
The UNT Digital Library
Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes
Report presenting the results of tests of a model of a single-engine airplane with two different tilts of the propeller axis. The results indicate that on a typical design, a 5 degree downward tilt of the propeller axis will considerably reduce the destabilizing effects of power.
Date:
November 1944
Creator:
Goett, Harry J. & Delany, Noel K.
System:
The UNT Digital Library
Investigation of the Behavior of Parallel Two-Dimensional Air Jets
Report presenting an investigation of the flow downstream from a two-dimensional grid formed of parallel rods. The nature of the flow was determined primarily by means of total-head measurements. Preliminary tests were made in both the closed-duct and open, two-dimensional configurations, but it was found that the same phenomenon occurred in both cases.
Date:
November 1944
Creator:
Corrsin, Stanley
System:
The UNT Digital Library
Wind-Tunnel Investigation of Ailerons on a Low-Drag Airfoil 3: The Effect of Tabs
Report presenting an investigation of the effects of 0.20-aileron-chord tabs on an NACA 66,2-216 airfoil equipped with a 0.20-airfoil-chord plain sealed aileron. Basic data are presented from which the effect of tabs can be calculated for specific cases. The data are sufficient for the solution of problems of fixed tabs with a differential linkage, as well as simple and spring-linked balancing tabs.
Date:
November 1944
Creator:
Holtzclaw, Ralph W. & Crane, Robert M.
System:
The UNT Digital Library