Author : John B. Parkinson
Publisher :
Page : 612 pages
File Size : 32,99 MB
Release : 1933
Category : Airplanes
ISBN :
N.A.C.A. 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 No. 11, the planing bottom of Model No. 11-A was made as flat as practicable. Otherwise, the two models have very nearly the same form.
Author : James M. Shoemaker
Publisher :
Page : 530 pages
File Size : 11,79 MB
Release : 1934
Category : Planing hulls
ISBN :
This report presents towing tests made in the N.A.C.A. tank of a parent form and five variations of a flying-boat hull. The beams of two of the dervied forms were made the same as that of the parent and the lengths changed by increasing and decreasing the spacing of stations. The lengths of two other of the derived forms were made the same as that of the parent while the beams were changed by increasing and decreasing the spacing of buttocks, all other widths being changed in proportion. The remaining derived form has the same length and beam as the parent, but the lines of the forebody were altered to give a planing bottom with no longitudinal curvature forward of the step.
Author :
Publisher :
Page : 184 pages
File Size : 13,69 MB
Release :
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 542 pages
File Size : 21,56 MB
Release :
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 1262 pages
File Size : 15,35 MB
Release : 1954
Category : Aeronautics
ISBN :
Author : Starr Truscott
Publisher :
Page : 586 pages
File Size : 23,62 MB
Release : 1938
Category : Drag (Aerodynamics)
ISBN :
N.A.C.A. models 74, 74-A, and 75 were tested in the N.A.C.A. tank to determine their hydrodynamic properties and in the N.A.C.A. 20-foot wind tunnel to determine their aerodynamic properties. The forms of these models were derived from that of a solid of revolution having a lowe air drag, and the departures from the form of this low-drag body were the minimum considered to give satisfactory take-off performance. Model 74 has a rounded bottom with flared chines, a transverse step wit ha small fairing aft of it, and a pointed afterbody. Model 74-A has the same forme except for the removal of the fairing aft of the step. Model 75 has a pointed step and a horizontal afterbody derived from the form of the N.A.C.A. model 35 series.
Author : Richard H. MacNeal
Publisher :
Page : 786 pages
File Size : 38,53 MB
Release : 1953
Category : Airplanes
ISBN :
Deflections and all internal forces have been calculated for concentrated static loads. Vibration modes are also presented. The effects of neglecting shearing strains in the ribs and spars and also of assuming the ribs to be rigid have been investigated by modifying the electric circuits to correspond to these simplifications.
Author : J. O. Hutton
Publisher :
Page : 582 pages
File Size : 24,2 MB
Release : 1941
Category : Aluminum alloys
ISBN :
The results of tests of 65 specimens of aluminum-alloy channel sections are graphed for stresses due to axial and bending loads as functions of the ratio of length of specimen to its radius of gyration, and from these data a suggested design chart is derived that is suitable for ready use.
Author : H. N. Hill
Publisher :
Page : 582 pages
File Size : 37,31 MB
Release : 1939
Category : Graphic methods
ISBN :
The method herein described is essentially graphical, but does require a small amount of arithmetical manipulation. It is not, however, a combination of the two methods mentioned above. To the best of the writer's knowledge, this treatment constitutes an entirely new procedure for determining stresses from strains measured on gage lines intersecting at 45 degrees. The method is thought to have some advantages in simplicity and directness over both of those previously mentioned.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 222 pages
File Size : 23,11 MB
Release :
Category : Aeronautics
ISBN :
