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1oVMAC 30 percent chord aeroelastic twist aileron airfoil section ALPHA POROSITY 0.8 angle of attack C-141 aircraft Cahill Compressible Flow Facility correlation data measured DATA REYNOLDS degree angle downstream pressures element line figures 12 flight data flight test FLOOR SEALED flow separation full-span fuselage geometric angle high Reynolds number highest Reynolds number inboard stations indicate Lockheed-Georgia Company low Reynolds numbers lower surface pressures NASA natural transition nondimensional number transonic wind oK ol oL L'Z orifices outboard stations panel model plots pressure coefficient pressure data pylons and nacelles range of Reynolds REYNOLDS NUMBER TESTS scale effects semispan model semispan test shock-induced separation shown in figure simulation span spanwise contamination spanwise distance spanwise flow spanwise station spanwise variation stagnation pressure station 389 station 637 SUPPORT TANG FAIRED sweep angle trailing-edge pressure recovery trailing-edge separation TRANSITION FIXED transonic wind tunnel UPPER UPPER velocity Wind Tunnel Model X 10VMAC