Normal gross weight G, weight of fuel and oil G
f+0 and necessary horsepower N
z or thrust T
z can readily be calculated by equations (4), (5), (6) or (10), (11), (12) respectively for propeller planes or jet planes, as the function of payload A, design load factor sn
A, range R and maximum velocity V
z at attitude z. The values of statistical constants a
i, b
i and numerical example are shown in appendices.
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