Multiple hour flight and delays on my way back to Canada, got to do some analysis of a classroom tutorial on turning performance. Part of it was the creation of a “doghouse” plot (indicating both sustained and instantaneous turning performance) for a fictional IF-35A. The doghouse is complete with the load factor and turn radius curves, and in a form which I consider to be appropriate for inclusion in an AFM.
There are few assumptions in the modeling performed to create this plot which may raise the eye brows of the most experienced readers of this blog… I am fully aware of those, but I will keep their identifications as a student exercise :)
(Shiba is there just for the joke of it, and to indicate why the shape of this plot is named as doghouse :)
Back from Hamburg and from an extensive day of testing. Overall I did well, but I don’t know if well enough to get me to the next stage.
There were tests I know I excelled, some others I did very good, some good and a couple of average. In the technical and math questions, my main concern was the time pressure. All subjects were within my capabilities, but for some I was not very sharp/fresh and that combined with the time pressure, the stress, the jet lag and even some ambiguous English language resulted in some slips which I though afterwards.
Anyway, overall I am satisfied and optimistic. I will accept any result positively.
My second article published in SETP’s Cockpit Magazine. Cockpit Magazine is a peer reviewed journal created to share the lessons learned and milestones of the Society of Experimental Test Pilots. The article looks in-depth in the wind-up-turn test technique flight dynamics and the effect of engine thrust.
The following part is from an article I recently submitted to be published in the SETP Cockpit magazine and follows up an analysis I had performed few years ago.
“To complete this analysis and quantify the effect of the thrust setting on ITR, a specific example is considered. The following figures (3 and 4) are analytically generated and correspond to a high-performance fighter aircraft assuming a 9g limit, a weight of 20,000kg, altitude 20,000 ft and max thrust at that altitude of 20,000lbs. The primary analysis considers a α_max of 50deg and δ=0 (Fig.3(a) and Fig,4(a)), and a sensitivity analysis is performed for α_max of 60 and 40 deg as well (Fig.3(b) and Fig,4(b)).“