A Summary of Transonic Natural Laminar Flow Airfoil Development at NAE

This report contains an analysis of the experimental results obtained from four supercritical natural laminar flow (NLF) airfoils investigated in the NAE High Reynolds Number Test Facility. The airfoils have maximum thickness to chord ratios of 0.10, 0.13, 0.16 and 0.21 and were designed for a lift coefficient of CL = 0.6. Their design Mach...

Further studies on the 21% thick, supercritical NLF airfoil NAE 68-060-21:1

Further wind tunnel tests have been carried out on the NAE 10" chord supercritical NLF airfoil NAE 68-060-21:1. This airfoil in previous tests showed very low drag levels when free transition was allowed on the model. In the main part of the current investigation, performed at chord Reynolds number of about 7,9 and 13 million, transition was...

Analysis of experimental data for a 21% thick natural laminar flow airfoil, NAE 68-060-21:1

NAE and de Havilland Aircraft of Canada have designed and tested in the NAE 5 ft X 5 ft wind tunnel a 21% thick supercritical airfoil capable of sustaining long runs of laminar flow on both surfaces. The measured drag levels are superior to those of any model previously tested in this facility and are comparabIe to classical NACA and modern NASA...