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Investigation of vertical drag and periodic airloads acting on flat panels in a rotor slipstream
- Author / Creator
- Available as
- Online
- Summary
-
Tests have been conducted on the Langley helicopter test tower to determine the vertical drag and pressure distributions on flat panels mounted below a helicopter rotor. Calculations of the vertica...
Tests have been conducted on the Langley helicopter test tower to determine the vertical drag and pressure distributions on flat panels mounted below a helicopter rotor. Calculations of the vertical drag by use of a strip-analysis procedure outlined in the paper and the assumption of a fully contracted wake agreed well with the experimental results over the range from 0.2 to 0.64 rotor radius beneath the plane of zero flapping. The pressure increase caused by the passage of the blade over the panel is a maximum at about the 0.8 radius spanwise station. At this station, the pressure decreases from 10 times the disk loading per blade at 0.05 radius beneath the rotor plane of zero flapping to one-half of the disk loading per blade at 0.64 radius beneath the plane of zero flapping.
Details
- Creator
- by Robert A. Makofski and George F. Menkick
- Included Title
-
- Technical Report Archive & Image Library (TRAIL)
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1957
- Physical Details
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- 1 online resource (23 pages) : illustrations, photographs
- data file
- OCLC
- on1417158214
- Report no. NACA-TN-3900.
- Date of issue: December 1956.
- "Langley Aeronautical Laboratory."
- Title from title screen (viewed September 5, 2023).
- Includes bibliographical references (page 11)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.