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A complete tank test of a model of a flying-boat Hull - N.A.C.A. model no.11-A

Description: Model No. 11-A was designed as an improvement over N.A.C.A. Model No. 11, a complete test of which is described in N.A.C.A. Technical Note No. 464. In contrast with the longitudinal upward curvature in the planing bottom forward of the main step on Model 11-A was made as flat as practicable. Otherwise, the two models have very nearly the same form. The results of towing tests made on Model 11-A in the N.A.C.A. tank over a wide range of speed, load on the water, and trim angle are presented, bot… more
Date: September 1933
Creator: Parkinson, John B.
Item Type: Refine your search to only Report
open access

A Complete Tank Test of a Model of Flying-Boat Hull - N.A.C.A. Model 16

Description: "A model of a 2-step flying-boat hull, of the type generally used in England, was tested according to the complete method described in the N.A.C.A. Technical Note No. 464. The lines of this model were taken from offsets given by Mr. William Munro in Flight, May 29, 1931. The data cover the range of loads, speeds, and trim angles that may be of use in applying the hull form to the design of any seaplane. The results are reduced to nondimensional form to aid application to design problems and fac… more
Date: September 1933
Creator: Shoemaker, James M.
Item Type: Refine your search to only Report
open access

The Effect of Partial-Span Split Flaps on the Aerodynamic Characteristics of a Clark Y Wing

Description: "Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a model Clark Y wing with a 20 percent chord split flap deflected 60 degrees downward. The tests were made to determine the effect of partial-span split flaps, located at various positions along the wing span on the aerodynamic characteristics of the wing-and-flap combination. The different lengths and locations of the flaps were obtained by cutting off portions of a full-span flap, first from the tips and then from … more
Date: September 1933
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
open access

Guide Vanes for Deflecting Fluid Currents With Small Loss of Energy

Description: The transverse momentum of the deflected air stream to be absorbed is divided between the intermediate and outside walls, so that the pressure increase on each wall is much smaller and the danger of separation is diminished. The formation of secondary vortices is also diminished. By taking as the basis profiles with high c(sub a), such as have proved practically favorable, it is not possible to find a satisfactory form of grid simply on the assumption that the flow is potential.
Date: September 1933
Creator: Kröber, G.
Item Type: Refine your search to only Report
open access

Results of Extended Tests of the Focke-Wulf F 19a "Ente," a Tail-First Airplane

Description: These investigations consisted chiefly of measurements of the take-off distance under various starting conditions and with the c.g. in different positions; of the climbing speed as a function of the impact pressure and location of the c.g.; of the longitudinal stability and fore-and-aft controllability and of the determination of the elevator forces and characteristics of the elevator control.
Date: September 1933
Creator: Hübner, Walter
Item Type: Refine your search to only Report
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