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Stall speed increases in proportion to the square root of the load factor. Thus, with a load factor of 4, an aircraft will stall at a speed which is double the normal stall speed.Answer (B) is incorrect because an airplane's tendency to spin does not relate to an increase in load factors. Answer (C) is incorrect because an airplane's stability determines its controllability.

The manufacturer is the best source of performance data and information, if available.

At slow speeds, the maximum available lifting force of the wing is only slightly greater than the amount necessary to support the weight of the sUAS. However, at high speeds, the capacity of the flight controls, or a strong gust, may increase the load factor beyond safe limits.Answer (A) is incorrect because the position of the CG affects the stability of the sUAS, but not the total load the wings can support. Answer (C) is incorrect because abrupt control inputs do not limit load.

The most critical conditions of launch performance are the result of some combination of high gross weight, altitude, temperature, and unfavorable wind. In all cases, the remote pilot must make an accurate prediction of takeoff distance from the performance data of the POH, regardless of the runway available, and strive for polished, professional launch procedures.

The maximum endurance condition is obtained at the point of minimum power required since this would require the lowest fuel flow or battery to keep the sUAS in steady, level flight. Maximum range condition occurs where the proportion between speed and power required is greatest.