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Boulton Paul P.71a Commercial Airplane (British): A Two-Engine Biplane

Description: Circular presenting a description of the Boulton Paul P.71A, which is a new type of two-engine biplane. Details of the design, fuel tanks, materials, fuselage, passenger seating, tail, and flying qualities are provided.
Date: March 1935
Partner: UNT Libraries Government Documents Department
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Calculations of the Effect of Wing Twist on the Air Forces Acting on a Monoplane Wing

Description: "A method is presented for calculating the aerodynamic forces on a moncylane wing, taking into account the elastic twisting of the wing due to these forces. The lift distribution along the span is calculated by the formulas of Amstutz as a function of the geometrical characteristics of the wing and of the twist at stations 60 and 90 percent of the semispan. The twist for a given lift distribution is calculated by means of influence lines" (p. 1).
Date: March 1935
Creator: Dätwyler, G.
Partner: UNT Libraries Government Documents Department
open access

Full-scale force and pressure-distribution tests on a tapered U.S.A. 45 airfoil

Description: This report presents the results of force and pressure-distribution tests on a 2:1 tapered USA 45 airfoil as determined in the full-scale wind tunnel. The airfoil has a constant-chord center section and rounded tips and is tapered in thickness from 18 percent at the root to 9 percent at the tip. Force tests were made throughout a Reynolds Number range of approximately 2,000,000 to 8,000,000 providing data on the scale effect in addition to the conventional characteristics. Pressure-distribution… more
Date: March 1935
Creator: Parsons, John F.
Partner: UNT Libraries Government Documents Department
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Tank tests of a model of a flying-boat hull with a fluted bottom

Description: A 1/5-scale model of a flying-boat hull having flutes in the bottom both forward and aft of the step (NACA model 19) was tested to determine its water performance. The model was also tested after the successive removal of the flutes on the afterbody and forebody. The results from these tests are compared with those from tests of a model of the hull of the Navy PN-8 flying boat and it is concluded that the fluted-bottom model and its modifications are inferior to the model of the PN-8.
Date: March 1935
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department
open access

The Bending of Beams With Thin Tension Flanges

Description: This report analyzes the action of a cantilever T beam with a tension flange so thin it can only carry tensile stresses.
Date: March 1935
Creator: Cicala, Placido
Partner: UNT Libraries Government Documents Department
open access

The Interdependence of Profile Drag and Lift With Joukowski Type and Related Airfoils

Description: "On the basis of a systematic investigation of Gottingen wind-tunnel data on Joukowski type and related airfoils, it is shown in what manner the profile drag coefficient is dependent on the lift coefficient. The individual factors for the construction of the profile drag polars are given. They afford a more accurate calculation of the performance coefficients of airplane designs than otherwise attainable with the conventional assumption of constant drag coefficient" (p. 1).
Date: March 1935
Creator: Muttray, H.
Partner: UNT Libraries Government Documents Department
open access

Modification of Wing-Section Shape to Assure a Predetermined Change in Pressure Distribution

Description: "In order to find an airfoil for a predetermined pressure distribution, the problem must be posed so that the pressure distribution creates no drag. Another fundamental difficulty is that it is impossible to specify a pressure distribution without first knowing the place where these pressures are to be applied, i.e., the wing-section shape. This difficulty may be avoided by directing the pressure distribution along the contour of the wing section. Then it becomes possible to define the change i… more
Date: March 1935
Creator: Betz, A.
Partner: UNT Libraries Government Documents Department
open access

The Aeronautical Laboratory of the Stockholm Technical Institute

Description: This report presents a detailed analysis and history of the construction and operation of the aeronautical laboratory of the Stockholm Technical Institute. Engines and balances are discussed and experimental results are also given.
Date: March 1935
Creator: Malmer, Ivar
Partner: UNT Libraries Government Documents Department
open access

A Turbulence Indicator Utilizing the Diffusion of Heat

Description: This report describes a method of determining the turbulence in wind tunnels. The effect of turbulence upon the diffusion of heat from a small electrically heated wire in an air stream was investigated. The turbulence of the stream was introduced by a series of geometrically similar screens placed one at a time across the upstream section of the tunnel. With the wire set at various distances from the screens, curves of temperature distribution were obtained by traversing the heated wake at a di… more
Date: March 8, 1935
Creator: Schubauer, G. B.
Partner: UNT Libraries Government Documents Department
open access

Characteristics of the NACA 23012 airfoil from tests in the full-scale and variable-density tunnels

Description: "This report gives the results of tests in the NACA full-scale and variable-density tunnels of a new wing section, the NACA 23012, which is one of the more promising of an extended series of related airfoils recently developed. The tests were made at several values of the Reynolds number between 1,000,000 and 8,000,000. The new airfoil develops a reasonably high maximum lift and a low profile drag, which results in an unusually high value of the speed-range index. In addition, the pitching-mome… more
Date: March 1, 1935
Creator: Jacobs, Eastman N. & Clay, William C.
Partner: UNT Libraries Government Documents Department
open access

Interference of wing and fuselage from tests of 209 combinations in the NACA variable-density tunnel

Description: This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA variable-density wind tunnel to provide information regarding the effects of aerodynamic interference between wings and fuselages at a large value of Reynolds number.
Date: March 8, 1935
Creator: Jacobs, Eastman N. & Ward, Kenneth E.
Partner: UNT Libraries Government Documents Department
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