Double hinged flap

Claim 1

IN A BOUNDARY LAYER CONTROL SYSTEM FOR AN AIRCRAFT HAVING WINGS WITH RELATIVELY LARGE CHORDS, THE COMBINATION COMPRISING: FLAP MEANS EXTENDING SUBSTANTIALLY THE LENGTH OF THE WING AND HAVING COMPLEMENTARY UPPER AND LOWER FLAP SEGMENTS; SAID FLAP SEGMENTS PIVOTED TO SAID WING ADJACENT THE UPPER AND LOWER SURFACES RESPECTIVELY AT FIXED POINTS THEREOF; LINKAGE MEANS PIVOTALLY INTERCONNECTED TO SAID FLAP SEGMENTS AND ACTUATOR MEANS; COMPRESSOR MEANS FOR A SUPPLY OF HIGH-PRESSURE FLUID; NOZZLE MEANS BETWEEN THE UPPER SURFACE OF SAID WING AND SAID UPPER FLAP SEGMENT; AND CONDUIT MEANS EXTENDING BETWEEN SAID COMPRESSOR MEANS AND SAID NOZZLE MEANS WHEREBY HIGH-PRESSURE FLUID FROM THE COMPRESSOR IS EXHAUSTED OVER THE UPPER FLAP SEGMENT TO EFFECTIVELY CONTROL THE BOUNDARY LAYER ALONG THE UPPER SURFACE OF THE WING AND THEREBY IMPART HIGH-LIFT CHARACTERISTICS TO THE WING REGARDLESS OF THE ORIENTATION OF THE AIRCRAFT.