CN201320833592.6U Airfoil with high lift force and high lift-drag ratio high lift airfoil with high ratio of lift over drag according to claim 1, is characterized in that, its maximal phase is to camber 2.25%～6.3%, maximum camber relative position 55% Maximum relative thickness 7.8%～18.2%, maximum ga(u)ge relative position 30%. 238000000926 separation method Methods 0.000 description 1Ĭompared with the up to ten million flight Reynolds number of conventional manned aircraft, during due to the long boat of low speed, the flight Reynolds number of unmanned plane is lower, flowing in its aerofoil profile is no longer to take as the leading factor with turbulent flow, but exist the transition flow of larger laminar region moving, be that laminar flow and turbulent flow coexist with magnitude, or even take as the leading factor with laminar flow.Although laminar flow can reduce friction drag to a great extent, it easily produces shunting bubble, causes separated flow, brings very strong pressure drag, thereby can balance out benefit, or even produce worse impact, makes the performance of aerofoil profile become extreme difference And in low reynolds number flow, although turbulent flow can increase friction drag, it can well suppress laminar flow separation bubble, avoid separated flow, play the effect that reduces pressure drag.Therefore, for such unmanned plane, its aerofoil profile profile must be coordinated the distribution of laminar flow and turbulent flow, makes aerofoil profile can at utmost bring into play the antifriction resistance effectiveness of laminar flow, can utilize well again turbulent flow compacting shunting, thereby realize the High Performance of aerofoil profile.Ģ.230000002349 favourable Effects 0.000 claims description 3.238000004458 analytical method Methods 0.000 claims description 3.Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Application filed by China Academy of Aerospace Aerodynamics CAAA filed Critical China Academy of Aerospace Aerodynamics CAAA Priority to CN201320833592.6U priority Critical patent/CN203681864U/en Application granted granted Critical Publication of CN203681864U publication Critical patent/CN203681864U/en Status Active legal-status Critical Current Anticipated expiration legal-status Critical Links
Original Assignee China Academy of Aerospace Aerodynamics CAAA 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.)Ĭhina Academy of Aerospace Aerodynamics CAAA
Inventor 刘强 刘欣煜 陈广强 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.) Active Application number CN201320833592.6U Other languages Chinese ( zh)
LOW SPEED HIGH LIFT AIRFOIL PDF
Google Patents Airfoil with high lift force and high lift-drag ratioĭownload PDF Info Publication number CN203681864U CN203681864U CN201320833592.6U CN201320833592U CN203681864U CN 203681864 U CN203681864 U CN 203681864U CN 201320833592 U CN201320833592 U CN 201320833592U CN 203681864 U CN203681864 U CN 203681864U Authority CN China Prior art keywords airfoil base profile lift high lift maximum Prior art date Legal status (The legal status is an assumption and is not a legal conclusion. Google Patents CN203681864U - Airfoil with high lift force and high lift-drag ratio
CN203681864U - Airfoil with high lift force and high lift-drag ratio
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