Investigation of Surface Irregularities on an NACA 63(420)-416, a = 1.0 Airfoil Section for the Glenn L. Martin Company Design 195
Abstract
The results of an investigation made in the NACA two-dimensional low-turbulence pressure tunnel of surface irregularities on a 60-inch-chord low-drag airfoil section are presented. Tests of riveted and piano-hinge-type skin joints at the front and rear spar locations (15-percent and 60-percent chord, respectively) in various combinations and modifications showed that either skin joint at the front spar, however treated, cause a substantial increase in drag, whereas irregularities at the rear spar caused no significant increase in drag so long as no leakage of air through the airfoil was present; leakage of air through the airfoil at either spar resulted in an additional increase of drag. An aileron slat installed on the lower surface of the airfoil caused no significant drag increment.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1943
- Accession Number
- ADA801417
Entities
People
- Albert L. Braslow
Organizations
- National Advisory Committee for Aeronautics