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010 "Worst" "Best" Both power curves and ES-2). At ES-1 minimum required the RPM's an same RPM 8900. RPM steady curves ES-4 and ES-5. The about 80 ft-lbf/s at about The probably are Astro 05 close of supplying power requirements for would suffice. 5 16 ft-lbf/s design (see ft-lbf/s table The 05 of 8790 in figures excess of the ounces ft/s, and both engines two engines is twice the gain will Given Furthermore, a 60% of of 50 for climbing. of 50 to available is in either by needs engines. speed, ES-3).
10 in, used two case the to drag and one a multiples given flight wing surface area, lift coefficient respectfully). 010 "Worst" "Best" Both power curves and ES-2). At ES-1 minimum required the RPM's an same RPM 8900. RPM steady curves ES-4 and ES-5. The about 80 ft-lbf/s at about The probably are Astro 05 close of supplying power requirements for would suffice. 5 16 ft-lbf/s design (see ft-lbf/s table The 05 of 8790 in figures excess of the ounces ft/s, and both engines two engines is twice the gain will Given Furthermore, a 60% of of 50 for climbing.
__ ___ / 17_)¢ i 5"0/t L. -] 27 Structural V-N Diagram The seen V-n in figure the nature 50 ft/s, the diagram (velocity St. 1. The maximum of the it was walls) Judged to Design judged inside the cruising velocity of 50 limit. A factor calculations facility. 6 due assumptions, be slightly loads for ft/s be to the from than (namely the at the value level below and different greater of 2 corresponds feet to an the flight design adequate upper inaccuracy the the be because of 4 is twice sufficiently chosen can obstacles factor determined 2 was to be 50 loading radius Penguin At velocities loading The therefore of for the defined difficult radius This beams beams The flight.