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Aerodynamic Noise And The Estimation Of Noise In Aircraft
Author(s): Rogers, Orville R., Cook, Robert F.
Corporate Author(s): Aircraft Laboratory
Laboratory: Aircraft Laboratory
Date of Publication: 1952-02
Report number: WADC TR 52-341
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Flight Test Investigation to Determine the Effectiveness of a Rocket as an Emergency Spin Recovery Device
Author(s): Farmer, G. H., Peterson, B. G.
Corporate Author(s): North American Aviation, Inc.
Laboratory: Aircraft Laboratory
Date of Publication: 1952-01
Report number: WADC TR 52-233
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Investigation of Discrepancies Between Flight-Measured and Calculated F-80A Derivatives and Respnonses Including a Study of Aeroelastic Effects
Author(s): Segel, Leonard
Corporate Author(s): Cornell Aeronautical Laboratory, Inc.
Laboratory: Aircraft Laboratory
Date of Publication: 1952-08
Report number: WADC TR 52-130
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Rolling Effectiveness and Aileron Reversal Characteristics of Straight and Sweptback Wings: Part 3. Evaluation and Test Results
Author(s): Groth, Eric
Corporate Author(s): Aircraft Laboratory
Laboratory: Aircraft Laboratory
Date of Publication: 1952-09
Report number: AF TR 6198 Part 3
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Measurements with Honeycombs in the Full-Scale and in the Model Vertical Wind Tunnel
Author(s): Knackstedt, Wilhelm F.
Corporate Author(s): Aircraft Laboratory
Laboratory: Aircraft Laboratory
Date of Publication: 1952-08
Report number: WADC TR 52-207
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Subsonic Flow Over a Body Between Porous Walls
Author(s): Kassner, Rudolph R.
Corporate Author(s): Wright Air Development Center
Laboratory: Aircraft Laboratory
Date of Publication: 1952-02
Report number: WADC TR 52-9
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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): Sechler, E. E., Beebe, W. M.
Corporate Author(s): Guggenheim Aeronautical Laboratory, California Institute of Technology
Laboratory: Aircraft Laboratory
Date of Publication: 1952-07
Report number: AF TR 5761 Part 16

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