4 Matching Results

Search Results

Results: 1 - 4
open access

Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers Up to 1.9

Description: "Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by 6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions" (p. 1).
Date: March 27, 1957
Creator: Petersen, Robert B.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Measurements of Atmospheric Turbulence at High Altitude as Determined From Acceleration Measurements on Lockheed U-2 Airplane

Description: "An analysis of a sample of turbulence data obtained from VGH records taken on Lockheed U-2 airplanes during research flight up to 55,000 feet over England and Western Europe has indicated substantial reductions in the number and intensity of gusts with increasing altitude. These results on the variation of atmospheric turbulence over England and Western Europe were found to be in overall agreement with previous turbulence data obtained from airplane- and balloon-borne instruments over the Unit… more
Date: March 27, 1957
Creator: Coleman, Thomas L. & Funk, Jack
Partner: UNT Libraries Government Documents Department
open access

Some characteristics of roll controls having possible application to fin-stabilized ammunition

Description: Report presenting a discussion of the rolling effectiveness of deflected fins, flaps, spoilers, and jet devices that can be used on fin-stabilized ammunition. The possible applications and some of the significant factors affecting the performance of each device are described. The selection of one control over another appears to be mostly designer's choice with some exceptions depending on the roll requirements in a given situation.
Date: March 27, 1957
Creator: Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
open access

Statistical Approach to the Estimation of Loads and Pressures on Seaplane Hulls for Routine Operations

Description: Memorandum presenting a study of the impact loads experienced during full-scale and model tests in order to estimate the repeated loadings of seaplanes for long operating periods. The results indicate that the low landing speeds for antisubmarine-warafare seaplanes reduced the magnitude of the loads but that the more frequent landings and take-offs required for these operations greatly increased the total number of loads.
Date: March 27, 1957
Creator: Steiner, Roy
Partner: UNT Libraries Government Documents Department
Back to Top of Screen