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The drag curve or drag polar is the relationship between the drag on an aircraft and other variables, such as lift, the coefficient of lift, angle-of-attack or speed. It may be described by an equation or displayed as a graph (sometimes called a "polar plot"). [1] Drag may be expressed as actual drag or the coefficient of drag.
The Cooper-Harper Handling Qualities Rating Scale [1] (HQRS), sometimes Cooper-Harper Rating Scale (CHRS), is a pilot rating scale, a set of criteria used by test pilots and flight test engineers to evaluate the handling qualities of aircraft while performing a task during a flight test. The scale ranges from 1 to 10, with 1 indicating the best ...
The flight test phase accomplishes two major tasks: 1) finding and fixing design problems and then 2) verifying and documenting the vehicle capabilities when the vehicle design is complete, or to provide a final specification for government certification or customer acceptance. The flight test phase can range from the test of a single new ...
An aircraft is streamlined from nose to tail to reduce drag making it advantageous to keep the sideslip angle near zero, though an aircraft may be deliberately "sideslipped" to increase drag and descent rate during landing, to keep aircraft heading same as runway heading during cross-wind landings and during flight with asymmetric power. [1]
It is measured empirically by testing in a wind tunnel or in free flight test. [1] [2] [3] The L/D ratio is affected by both the form drag of the body and by the induced drag associated with creating a lifting force. It depends principally on the lift and drag coefficients, angle of attack to the airflow and the wing aspect ratio.
Each certification level features unique criteria published by the FAA both electronically and in hard copy format. The system was partially superseded, beginning on June 15, 2016 ( 2016-06-15 ) , by a new set of publications called Airman Certification Standards , though the PTS is still used for select FAA practical tests.
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The stalling angle of attack is less in ground effect, by approximately 2–4 degrees, than in free air. [23] [24] When the flow separates there is a large increase in drag. If the aircraft overrotates on take-off at too low a speed the increased drag can prevent the aircraft from leaving the ground.