Original Assignee Boeing Co Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Cole Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Expired - Lifetime Application number US05/708,671 Inventor James B. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.- Google Patents US4053124A - Variable camber airfoilĭownload PDF Info Publication number US4053124A US4053124A US05/708,671 US70867176A US4053124A US 4053124 A US4053124 A US 4053124A US 70867176 A US70867176 A US 70867176A US 4053124 A US4053124 A US 4053124A Authority US United States Prior art keywords airfoil trailing edge chordwise rib camber Prior art date Legal status (The legal status is an assumption and is not a legal conclusion. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. įor example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.
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