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in creator/contributor: "Pierce, Harold B."  
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Gust-tunnel investigation of a wing model with semichord line swept back 60 degrees

Description: Report presenting an investigation in the gust tunnel of a 60 degree sweptback-wing model to determine the effect of a large angle of sweep on gust loads. A simplified method of analysis, which uses a slope of the lift curve derived by the cosine law and which uses strip theory to estimate the penetration effect, appears to be applicable to the prediction of gust loads on wings swept as much as 60 degrees.
Date: October 1950
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Gust-tunnel investigation of a 45 degree sweptforward-wing model

Description: "The results of tests made in the Langley gust tunnel on a 45 degree swept-forward-wing model show that the acceleration increment obtained in a gust can be satisfactorily predicted from a slope of the lift curve obtained by multiplying the slope of the lift curve of the equivalent straight wing by the cosine of the angle of sweep and by using strip theory to estimate the penetration effect" (p. 1).
Date: October 1948
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a 45 degree sweptback-wing model in the Langley gust tunnel

Description: Report presenting a series of tests of a 45 degree sweptback-wing model with and without fuselage and an equivalent straight-wing model in the gust tunnel to provide information on some of the problems encountered in the prediction of gust loads for airplanes incorporating swept wings.
Date: February 1948
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic stress calculations for two airplanes in various gusts

Description: Report presenting a series of calculations made to determine the probable dynamic wing stress of two large airplanes in atmospheric gusts. The results indicate that in both isolated and repeated gusts of probable occurrence, the dynamic overstress is about 10 percent when referred to the present static design standard.
Date: September 1941
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the dynamic response of airplane wings to gusts

Description: Report presenting a method of predicting the dynamic response of airplane wings to gusts by considering only the fundamental mode of bending along with the results of model tests to evaluate the method. Results regarding experimental results and associated calculations, limitations of calculations, and results calculated for effect of change of certain parameters are provided.
Date: June 1947
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Gust-tunnel tests to determine influence of airfoil section characteristics on gust-load factors

Description: Report presenting gust-tunnel testing to determine if gust-load factors for airplanes with low-drag wing sections should be higher than those for airplanes with conventional wing sections. A model with a wing with a low-drag section was used with smooth surfaces and with roughness applied to the leading edge to simulate the flow conditions for a conventional section.
Date: July 1948
Creator: Pierce, Harold B. & Trauring, Mitchell
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Gust-Tunnel Investigation of a Delta-Wing Model With the Leading Edge Swept Back 60 Degrees

Description: Report discussing an investigation of a delta-wing model with the leading edge swept back 60 degrees. Testing indicated that the gust load is greater than would be predicted by using a slope of the lift curve determined from steady-flow force tests. An aspect-ratio relation was determined for this type of wing with the selected apex angle, but it does not appear to be applicable to other wings with different apex angles.
Date: April 9, 1952
Creator: Pierce, Harold B. & Johns, Slaton L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculations of the Dynamic Stress of Several Airplane Wings in Various Gusts

Description: "A series of calculations of the dynamic response of airplane wings to gusts were made with the purpose of showing the relative response of a reference airplane, the DC-3 airplane, and of newer types of airplanes represented by the DC-4, DC-6, and L-49 airplanes. Additional calculations were made for the DC-6 airplane to show the effects of speed and altitude. On the basis of the method of calculation used and the conditions selected for analysis, it is indicated that: 1) The newer airplanes sh… more
Date: July 12, 1948
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements and Analysis of the Motion of a Canard Airplane Model in Gusts

Description: Report presenting a model of a hypothetical canard airplane, which was designed to be of the same size and general aerodynamic characteristics of a Boeing B-247 airplane in the gust tunnel at one wing loading, one forward speed, one gust velocity, and three gust gradients.
Date: April 1940
Creator: Donely, Philip; Pierce, Harold B. & Pepoon, Philip W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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