Date of Award

5-2021

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Aerospace, Physics, and Space Sciences

First Advisor

Brian A. Kish

Second Advisor

Markus Wilde

Third Advisor

Isaac Silver

Fourth Advisor

David Fleming

Abstract

The objective of the performance profile and flight testing comparison is to practice flight test theory on a turbofan-powered aircraft, compare results to Dassault published parameters, and give insight on how this may become a module for the flight test engineering program at Florida Tech. The performance experiments conducted were takeoff performance, level acceleration, level flight performance, stall speed, and roll performance. Takeoff distance was observed using the data from the Stratus ADSB receiver, which gave GPS coordinates; additionally, takeoff distance was measured via Google Earth from the start and the takeoff location observed by the co-pilot. The takeoff field required was calculated to be 3,474 ft, 2% lower than the published FAR Part 25 takeoff distance. Level acceleration experiments were completed at two altitudes 10,500 ft and 17,000 ft. Level accelerations were carried out by taking the aircraft nearly to stall, then doing a 100% throttle input until a steady state speed was achieved. Level flight performance was conducted using the constant 𝑊𝛿method. An initial 𝑊𝛿was observed at14,500 ft at M = 0.7 for 60 seconds. For the next data point, a new altitude was calculated to correspond with the proper delta required to keep 𝑊𝛿constant since weight decreases as fuel is burned. A determination of stall speed was observed; however, a clean stall was not possible on the Dassault Falcon-10 since there is a stall prevention system that deploys slats automatically. The lowest speed observed was 90 knots. Roll performance was inspected by doing 45-to 45 rolls and taking the time to get from 30 ̊ LWD to 30 ̊ RWD and vice versa. The average time to roll was 0.68 seconds with and average roll rate of 88 degrees per second.

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