Diseño de Aeronaves
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Un problema basico de diseño de aeronaves
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DATOS 0.125W(kg) 360S(m^2) 18AR 20
N P(mm Hg) T(R)1 570 271.152 560 273.153 590 275.154 610 277.155
620 279.156 640 281.157 660 283.158 680 274.152
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Vi(m/s) Wz(m/s) (1/) Vr (m/s) (GRADO)38.8888888889 3.85
0.79702194 1.1201208 43.5602532 5.07060775
27.5 1.44 0.7773057 1.13423769 31.1915364 2.6460786522.5 1.04
0.81299435 1.10906305 24.9539187 2.38859777
20 0.77 0.83448778 1.09468712 21.8937424 2.0155005717.5833333333
0.675 0.84209112 1.08973389 19.1611542 2.0188060914.8055555556 0.62
0.86307178 1.07640707 15.9368047 2.2295780714.8611111111 0.65
0.88375605 1.06373586 15.8082968 2.35653209
7.0833333333 0.77 0.94042145 1.03119011 7.30426325
6.05124337
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U(m/s) CL CD43.3897817 0.21076378 0.0187011931.1582789
0.42268933 0.0195348624.9322373 0.63154956 0.0263438721.8801978
0.79950508 0.0281358919.1492612 1.03437477 0.03646109
15.92474 1.45871907 0.056792515.7949279 1.44770469
0.05957667.26356397 6.34231734 0.67233997
TAREA 1
