FLIGHT TESTING OF THE MARVEL AND MARVELETTE AIRFOIL SECTION
Abstract
Airfoil sections for low speed flying need to be highly cambered with the point of maximum camber well forward to ensure low pitching moments whereas for maximum cruise speeds a thin low cambered airfoil is required. To satisfy both requirements, a compromise was reached in the form of a variable cambered airfoil. The uncambered airfoil was an excellent airfoil for the cruise condition due to its low drag and, when cambered, the airfoil was very suited to high lift coefficient flying. To ensure maximum utilization of the fully cambered wing, a turbulent high lift boundary layer control system was necessary to prevent turbulent boundary layer separation. The airfoil was a combination of low drag airfoil sections both forward and aft of the spar with an increase in leading edge radius in an attempt to prevent laminar separation at high angles of attack. When the airfoil is in the cambered position, however, only the section forward of the spar retains its original shape and with the flight loads on the relatively flexible wing, it would be difficult to pin down the exact coordinates of the airfoil. Results of flight testing of this MARVEL airfoil glove section are reported. Comparison is made between theory and experimental results.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1962
- Accession Number
- AD0295082
Entities
People
- Sean C. Roberts
Organizations
- Mississippi State University