General Aviation Aircraft-Normal Acceleration Data Analysis and Collection Project

Details

• Creators:
  Locke, James E. ; Smith, Howard W. ; Gabriel, Edward A.
• Corporate Creators:
  University of Kansas Flight Research Laboratory
• Corporate Contributors:
  United States. Department of Transportation. Federal Aviation Administration. Technical Center
• Subject/TRT Terms:
  • Aerodynamics
  • Airplanes
  • Airworthiness
  • Maintenance
• Publication/ Report Number:
  DOT/FAA/CT-91/20
• Resource Type:
  Tech Report
• Geographical Coverage:
  United States
• Edition:
  Final Report
• Corporate Publisher:
  United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
• Abstract:
  This report contains the analysis and condensation of repeated flight loads obtained from 77 airplanes that participated in the NASA Velocity Gravity Height (VGH) General Aviation Program. In addition, the load spectra for 98 airplanes in the NASA VGH data base are presented as plotted and tabulated data. Curve fit equations are listed for the original data and for extrapolation, which was used in the statistical analysis. Airspeed, normal load factor, and altitude were recorded continuously during flight. The load factor data were separated into gust and maneuver normal accelerations. The reduced data are presented as cumulative number of occurrences per nautical mile versus acceleration fraction (incremental normal acceleration divided by incremental limit load factor). For statistical analysis, the airplanes were grouped into seven single and twin-engine operational usage groups. The mean (weighted by flight time), weighted mean--plus one, two, and three standard deviation spectra, and the 90 percent probability/95 percent confidence spectra were determined for each operational usage group and for several of the groups combined. An estimate of the scatter associated with groups having small sample size was determined by computing a pooled variance and pooled standard deviation. The resulting load spectra are to be used for wing fatigue test or safe-life estimation. The Federal Aviation Administration's plans for further study using the results of this report are discussed. The final objective of this effort is to produce a revised fatigue evaluation report for small and commuter airplane certification under Part 23 of the Federal Aviation Regulations.
• Format:
  PDF
• Download URL:
  https://rosap.ntl.bts.gov/view/dot/93301/dot_93301_DS1.pdf
• File Type:
  [PDF - 17.76 MB]
• Collection(s):
  FAA William J. Hughes Technical Center for Advanced Aerospace
• Main Document Checksum:
  urn:sha-512:4439a5893ea81e7d069ac6cb06bf0aebadbc58928a196eeab95d8cdd4ba0d71006fd4b32891d4b72da77aaae51702cb8ed2b5203f27e42e7fefeaf4a13a12039