This experimental work was done as a research project at the United States Naval Academy Aerospace Engineering Department during 1981 while Jett was a Midshipman 1/C. I was the Academic Advisor. Professor Bernard Carson contributed to the theoretical part of the research. (I reset the paper and made one or two minor corrections.)
Dave Rogers

Turnback after engine failure is a three-dimensional multiple variable performance problem with multiple geometric constraints.

The turnback maneuver is cast as alternate asymptotic vertical plane boundary value problems. Both failure altitude and runway length are considered as unknown boundary conditions.

The turnback maneuver is categorized on whether the failure altitude distance is more or less than four turn radii from the runway departure end.

The performance elements of the maneuver are estimated from data in the pilot operating handbook (POH).

Three aircraft, an E33A Bonanza, a Cessna 172M and an Aeronca 7AC, are used as illustrative examples. The ratio of the climb to glide flight path angle emerges as the predictor of success, or failure. If the ratio is more than one, a properly flown maneuver is generally successful. If the ratio is less than one, a successful maneuver is generally limited to a small range of failure altitudes and runway lengths or is unsuccessful. This ratio, easily determined from POH information, strongly predicts success or failure.

Pilots should know which option physics favors. (531k pdf file).

This article estimates the angle of attack cushion for various speeds from 5% to 30% above stall speed. Three typical light general aviation aircraft are considered.