National Research Council of Canada. National Aeronautical Establishment. High Speed Aerodynamics Section.

• Lift on A Two-Dimensional Augmentor Wing
• Parametric Approximation For Incompressible Laminar Boundary Layers with Suction or Injection
• Perturbations on Simple Wedge Flow Relating to Axisymmetric Hypersonic Intakes or Imploding Cylindrical Shocks
• Rocket Experiments on the Heat Transfer to A Protuberance and to A Cavity
• Similar Solutions of Three-Dimensional Incompressible Laminar Boundary Layers with Suction and Injection
• Small Cross-Flows in Three-Dimensional Laminar Boundary Layers with Suction or Injection
• Some Additional Low Speed Bird Impact Tests on A Modified Windshield of the cl-41 Tutor Aircraft
• Three-Dimensional Flow Separation of A Plane, Incompressible, Laminar Boundary Layer Caused by A Half-Delta Wing on A Flat Plate
• Three-Dimensional Laminar Boundary-Layer Separation on A Flat Plate Due to A Flow Confrontation with A Half Cone at Incidence