Assertion: fuselage's lift coefficient | /r/HasProperty | c lf
Facets:
Source sentences:
text: Each pressure distribution can be summed or integrated to determine each surface's contribution to the total lift, positive or negative (up or down, respectively) and the fuselage's lift coefficient (C LF ) can be determined to a high degree of accuracy (±0.01), particularly at cruise speeds.
text: Another object of the invention is to provide an aircraft in which (a) the fuselage lift coefficient is 0.03 or less at an altitude between 25,000 and 51,000 ft. ISA in level flight at a speed of 0.5 to 0.95 IMN, while at minimum calibrated airspeed in level flight at sea level ISA, the fuselage lift coefficient (CL F ) is at least 0.60, preferably 0.70 to 4.0.
text: Below 0.33 the α-lift from the fuselage is insufficient to provide a lift coefficient (C LF ) of at least 0.50 at α ZLo =10°.
text: Any down force produced by a T-tail also reduces the calculated amount of fuselage lift and the corresponding lift coefficient, C LF .
text: Below 0.33 the α-lift from the fuselage is insufficient to provide a lift coefficient (C LF ) of at least 0.50 at α ZLo =10°.
text: Any down force produced by a T-tail also reduces the calculated amount of fuselage lift and the corresponding lift coefficient, C LF .
text: Each pressure distribution can be summed or integrated to determine each surface's contribution to the total lift, positive or negative (up or down, respectively) and the fuselage's lift coefficient (CL F ) can be determined to a high degree of accuracy (±0.01), particularly at cruise speeds.