A three-dimensional-membrane-type wing is investigated applying fluid-structure-interaction computations and complementary experiments.An analysis for three Reynolds numbers is conducted at various angles of attack.Th...A three-dimensional-membrane-type wing is investigated applying fluid-structure-interaction computations and complementary experiments.An analysis for three Reynolds numbers is conducted at various angles of attack.The computations are performed by means of the TAU-Code and the FEM Carat++solver.Wind-tunnel tests are carried out for performance analysis and to estimate the accuracy of the computations.In the results,the advantages of an elasto-flexible-lifting-surface concept are highlighted by comparing the formvariable surface to its rigid counterpart.The flexibility of the material and its adaptivity to the freestream allow the membrane to adjust its shape to the pressure distribution.For positive angles of attack,the airfoil’s camber increases resulting in an increase in the wing lifting capacity.Furthermore,the stall onset is postponed to higher angles of attack and the abrupt decrease in the lift is replaced by a gradual loss of it.展开更多
基金The authors would like to thank the German Research Association for the funding of the project BR 1511/10-1.
文摘A three-dimensional-membrane-type wing is investigated applying fluid-structure-interaction computations and complementary experiments.An analysis for three Reynolds numbers is conducted at various angles of attack.The computations are performed by means of the TAU-Code and the FEM Carat++solver.Wind-tunnel tests are carried out for performance analysis and to estimate the accuracy of the computations.In the results,the advantages of an elasto-flexible-lifting-surface concept are highlighted by comparing the formvariable surface to its rigid counterpart.The flexibility of the material and its adaptivity to the freestream allow the membrane to adjust its shape to the pressure distribution.For positive angles of attack,the airfoil’s camber increases resulting in an increase in the wing lifting capacity.Furthermore,the stall onset is postponed to higher angles of attack and the abrupt decrease in the lift is replaced by a gradual loss of it.
