Contrails
The goal of the Contrails project is to help preserve and disseminate the technical record of 20th century aerospace research, highlighting in particular the research endeavors of the Illinois Tech community.

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7 reports

Aerodynamic Noise And The Estimation Of Noise In Aircraft

Author(s): Orville R. Rogers, Robert F. Cook
Corporate Author: Aircraft Laboratory
Laboratory: Aircraft Laboratory
Date of Publication: 1952-02
Report Number: WADC TR 52-341
AD Number: AD0013026
full text available

Subsonic Flow Over a Body Between Porous Walls

Author(s): Kassner, Rudolph R.
Corporate Author: Wright Air Development Center
Laboratory: Aircraft Laboratory
Date of Publication: 1952-02
Report Number: WADC TR 52-9
full text unavailable

Flight Test Investigation to Determine the Effectiveness of a Rocket as an Emergency Spin Recovery Device

Author(s): G. H. Farmer; B. G. Peterson
Corporate Author: North American Aviation, Inc.
Laboratory: Aircraft Laboratory
Date of Publication: 1952-01
Report Number: WADC TR 52-233
full text unavailable

Investigation of Discrepancies Between Flight-Measured and Calculated F-80A Derivatives and Respnonses Including a Study of Aeroelastic Effects

Author(s): Leonard Segel
Corporate Author: Cornell Aeronautical Laboratory, Inc.
Laboratory: Aircraft Laboratory
Date of Publication: 1952-08
Report Number: WADC TR 52-130
full text by request

Rolling Effectiveness and Aileron Reversal Characteristics of Straight and Sweptback Wings: Part 3. Evaluation and Test Results

Author(s): Eric Groth
Corporate Author: Aircraft Laboratory
Laboratory: Aircraft Laboratory
Date of Publication: 1952-09
Report Number: AF TR 6198 Part 3
AD Number: AD0003719
full text unavailable

Measurements with Honeycombs in the Full-Scale and in the Model Vertical Wind Tunnel

Author(s): Wilhem F. Knackstedt
Corporate Author: Aircraft Laboratory
Laboratory: Aircraft Laboratory
Date of Publication: 1952-08
Report Number: WADC TR 52-207
AD Number: AD0008717
full text unavailable

Theoretical and Experimental Effect of Sweep upon the Stress and Deflection Distribution in Aircraft Wings of High Solidity: Part 16. Stress and Deflection Tests on Two Full Span 45 Degree Swept Plates of Different Thickness Distribution With Various Support Conditions

Author(s): E. E. Sechler; W. M. Beebe
Corporate Author: Guggenheim Aeronautical Laboratory, California Institute of Technology
Laboratory: Aircraft Laboratory
Date of Publication: 1952-07
Report Number: AF TR 5761 Part 16
full text unavailable