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Exercicio de aerodinamica

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Exercicio de aerodinamica
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  Estaçãoy (m)L(y) E (N/M)L(y) T (N/m)L(y) TS (N/M)1-60.001500.00750.002-51319.641625.001472.323-41779.411750.001764.704-32067.481875.001971.245-22250.792000.002125.406-12353.932125.002239.47702387.322250.002318.66812353.932125.002239.47922250.792000.002125.401032067.481875.001971.241141779.411750.001764.701251319.641625.001472.321360.001500.00750.00Distribuição de sustentação na asa 0.00500.001000.001500.002000.002500.003000.00-6-5-4-3 Aplicaçã L(y) E  -2-10123456  da aproximação de Schrenk (N/M)L(y) T (N/m)L(y) TS (N/M)  b12Cr1.8Ct1.2Peso total ( W) N9000Cond.atmosfera1.225n max2.5-6Força de Sustentação (N)225000.67L(y) e (-6)0.001500.00L(y) e (-5)1319.641625.00L(y) e (-4)1779.411750.00L(y) e (-3)2067.481875.00L(y) e (-2)2250.792000.00L(y) e (-1)2353.932125.00L(y) e (0)2387.322250.00L(y) e (1)2353.932125.00L(y) e (2)2250.792000.00L(y) e (3)2067.481875.00L(y) e (4)1779.411750.00L(y) e (5)1319.641625.00L(y) e (6)0.001500.00Caractristicas da aeronaveRelação de afilamento da Asa
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