High camber airfoil4/8/2023 ![]() ![]() The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. Y02T50/00- Aeronautics or air transportĪ variable camber apparatus for the leading and/or trailing edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft.Y02T- CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION.Y02- TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE.Y- GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS AND DIGESTS.B64C3/48- Varying camber by relatively-movable parts of wing structures.B64C3/38- Adjustment of complete wings or parts thereof.238000006011 modification reaction Methods 0.000 description 8. ![]() Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Priority claimed from US05/607,004 external-priority patent/US3994452A/en Application filed by Boeing Co filed Critical Boeing Co Priority to US05/708,671 priority Critical patent/US4053124A/en Application granted granted Critical Publication of US4053124A publication Critical patent/US4053124A/en Anticipated expiration legal-status Critical Status Expired - Lifetime legal-status Critical Current Links 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. Therefore, bi-cambered airfoil effectively lowers local Reynolds number is respect to boundary layer development.- Google Patents US4053124A - Variable camber airfoilÄownload 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. These characteristics provide extensive possibilities in designing the airfoil for a high altitude aircraft where the stalling angle is low due to thin air and in wind turbines where the high angle of attack flow is common. Bi-camber surface airfoil tends to attach a boundary layer at the second cambered surface of the airfoil, which results in improving aerodynamic characteristics. Rather than a single reflexed cambered surface with one, two, or more convex or concave curves may be used in the design of an airfoil. The current aim of this research is to enhance the aerodynamic efficiency to meet the outcome of the useful results. An improved airfoil contour has been designed with two ridges on the upper surface and a flat bottom-placed laterally to fluid flow, which is running from leading edge to trailing edge and is named a bi-cambered airfoil. The present research provides a design criterion for a stable airfoil at a high angle of attack. With the advancement of aerodynamics shapes, designing an airfoil contour is still a basic structure in fluid machinery. ![]() Sashant Kapoor, Vipin Kumar, Harshit Shukla, Kumar Gaurav and Dalbir Singh Abstract ![]()
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