Hi! Last year I saw JAXA rocket lunched Mach 2 glider for SST technology verificaiton, there are no suction holes at leading edge of the wing. It's natural laminar flow wing. Natural means no additional devices are needed for laminar flow.PNorwood said:blackkite,
I was under the impression that you would require boundary flow suction on the leading edge with the rest of the wing designed as a natural laminar-flow wing
blackkite said:Hi! Last year I saw JAXA rocket lunched Mach 2 glider for SST technology verificaiton, there are no suction holes at leading edge of the wing. It's natural laminar flow wing. Natural means no additional devices are needed for laminar flow.
The results are presented for the Douglas Aircraft Company system studies related to high speed civil transports (HSCTs). The system studies were conducted to assess the environmental compatibility of a HSCT at a design Mach number of 3.2. Sonic boom minimization, exterior noise, and engine emissions were assessed together with the effect of a laminar flow control (LFC) technology on vehicle gross weight. The general results indicated that (1) achievement of a 90 PLdB sonic boom loudness level goal at Mach 3.2 may not be practical; (2) the high flow engine cycle concept shows promise of achieving the side line FAR Part 36 noise limit but may not achieve the aircraft range design goal of 6,500 nautical miles; (3) the rich burn/quick quench (RB/QQ) combustor concept shows promise for achieving low EINO(sub x) levels when combined with a premixed pilot stage/advanced technology high power stage duct burner in the P and W variable stream control engine (VSCE); and (4) full chord wing LFC has significant performance and economic advantages relative to the turbulent wing baseline.
Current activities on the High Speed Civil Transport (HSCT) at Douglas are focussed on baseline vehicle development at Mach 1.6 and 2.4. Parallel design activities incorporating the latest technologies in structures/materials, propulsion/noise, and aerodynamics are also being conducted and incorporated into the baseline to establish performance, economic viability, and environmental compliance. Studies are also being conducted to establish the feasibility of incorporating laminar flow control and minimized sonic boom concepts into the baseline. A decision point on these last two technologies is targeted prior to the start of the NASA HSR Phase 2 Program in 1993.
Source: "New Aerodynamic Design, New Engines, Spawn a Revival of the SST" by Jim Shefter, Popular Science, July 1979.
Triton said:Model of Boeing SST concept circa 1979 with blended body. The blended body means that there are no windows in the passenger compartment. Passengers would have video monitors at each seat offering entertainment programs or outside views.
The inward leaning intakes are just aligning themselves with the airflow over the top of the wing.Stargazer2006 said:Nice, but the inward leaning intakes are extremely strange, I dare say...