The effect of rotor forward speed on the propulsive characteristics of a blade-tip-mounted helicopter-type pulse-jet engine has been deter¬mined in the Langley full-scale tunnel for various engine rotational speeds.nThe effect of forward speed was to decrease mean engine thrust and increase engine specific fuel consumption. For a representative cruising forward-flight condition of 90 feet per second and an engine velocity of about 570 feet per second, a reduction in propulsive thrust of about 5.5 percent and an increase in minimum specific fuel consumption of about 4 percent from that obtained at zero forward speed are shown.
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