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Effect of Taper Ratio on the Low-Speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2.61

Description: Report discussing testing on a series of tapered swept wings under conditions simulating rolling flight. The lift, longitudinal-force, and pitching-moment characteristics for three swept wings are provided. The results indicated that a decrease in taper ratio on a swept wing caused a small decrease in damping in roll at low and moderate lift coefficients.
Date: November 9, 1948
Creator: Brewer, Jack D. & Fisher, Lewis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of high-lift devices on the low-speed stability of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow

Description: Contains results of tunnel tests to determine effects of various combinations of split flaps, slats, and nose slats on the stability characteristics of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow.
Date: November 9, 1948
Creator: Queijo, M. J. & Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61

Description: Report presenting an investigation in the stability tunnel to determine the effect of airfoil profile on symmetrical sections on the static- and yawing-stability derivatives of three untapered wings of 45 degrees sweepback. All of the wings had an aspect ratio of 2.61. Results regarding the characteristics in straight flow, yawing flow, and drag index are provided.
Date: November 9, 1948
Creator: Letko, William & Jaquet, Byron M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The calculation of downwash behind supersonic wings with an application to triangular plan forms

Description: A method is developed consistent with the assumptions of small perturbation theory which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The equivalence in subsonic and supersonic flow of the downwash at infinity corresponding to a given load distribution is proved.
Date: November 9, 1948
Creator: Lomax, Harvard; Sluder, Loma & Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Density of metallic polonium (Information Meeting Paper No. 13)

Description: This document is the report from a November 1948 meeting at Mound Laboratory on the measurement of the density of metallic polonium. Four determinations of the density of Polonium at 25 degrees C have been made. These values are 8.69 gm/cc, 9,34 gm/cc (twice) and 9.20 gm/cc. The probable error was 2%. The material used in the first determination was not subjected to a preliminary purification, which makes the value obtained doubtful. In this instance, production foils were used without a separa… more
Date: November 9, 1948
Creator: Haring, M. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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