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AEROSERVOELASTICITY OF FIXED AND ROTARY WING AIRCRAFTComplete set

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University: Politecnico di Milano
Degree programme: Aerospace Engineering
Subject: AEROSERVOELASTICITY OF FIXED AND ROTARY WING AIRCRAFT
Classification: Exercises · Complete set
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Aeroservoelasticity of ﬁxed and rotary wing aircraft exercises Static and dynamic stability of the typical section model EXERCISE 1 : 3 4 1 d'G>☐ CASE CL • PROCEDURE: TAKE TVVO MEASUREMENTS OF Cl at ✗1,✗2 THE SLOPEWILL BECOMPUTEDASi [la= CL ✗ e • La= 1e a SÙSCLSXO ✗1 ✗2 ✗ ELASTIC CASE . La = 9Scettro L- La= ascia@= 0 La 9542×0 Lo• L = 95CLa/Lo+0) cnn.ca?E?9º e d • Kao= qsec.ca/0taolt9ScCnac ⊖= 9seccato Kx- 95ella • L- La= CL- CLR = 95Ecco ✗☐ . 1 = 9ha = ^ = 1 La Cera KX- 95ECLX ✗◦ Ka- Ata ka - 1 QD- 1 aka 9 2 • IF E= 0 KA= Secca= o L- Lr = ^ = 0 E= 0 La Cnac .ac≥EA CG. K✗ - y aka d 0 3 • considera an in/TIAL MUMENT MO= 95C(LO t 95C(MAC ELASTIC DEFORMATI0N : 00= Mo ka AEROELASTIC DEFORMATI0N: ⊖= Mo ka- 9KA MO AEROELASTIC PERFORMANCEINDEX : ⊖= '<×- 9'<a = 1 ⊖= 1 Oo OoMo 1- qKA 1- 9 Ka ka 90 DIUETZGENCE DYNAMIC PLESSURE '5 THE VARIABLE THAT HIGHLIGHTS THE IMPORTANCEOF THE AEROELASTIC EFFECTS THE MORE ofTENDS TO QDTHE MORE AEROELASTIC EFFECTS ARE RELEvani 4 L- La= E = 1 < z . . La KX - 1 aka ULIM= 2, 5090 M S 5 6 5 • E= 0 • KA = 01Secca = o • EQUIVALENT STIFFNESS : È= KX- QKa = O AD= KX 00 no ☐IVERGENCE ÷ ° , , , , C2 C2 C2 C2 C 4 C 4 C 4 - - AC. EA. AC... ....EA EAEAC. E= - C G:0_ C.= C4 E=0

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