Sure, if you can provide any credible evidence stating that the exact material discussed in the patent has a RDP suitable for application at a 3 times greater depth than the test examples…
This scalability is a valid issue you raised earlier for which I had no (at least publically revealable) answer beforehand. However, that was then.
This Russian company (SKB ‘Electron’/СКБ “Электрон”) has demonstrated CNT RAM of similar (probably identical ‘recipes’), achieving -6 to -8dB absorption for 0.6 to 0.8 mm thickness:
http://www.vesti.ru/doc.html?id=1140846
http://youtu.be/vPXXVyy6raI. (from 02:00)
The NPO Saturn/Lyulka CNT RAM attains -15dB absorption for 1.5mm- so the evidence is clear: the absorption efficiency vis-à-vis material thickness is directly proportional and NOT logarithmic.
One issue with your source is that article includes a diagram stating the effectiveness of the material at the lower end of x-band is merely -7dB. LO aircraft with a 20 – 30dBsm advantage due to shaping + similar materials (all US and Chinese examples) are detected at 1/3rd – 1/5th the range.
This proportionality would mean for all of 5mm the absorption average is going to be in excess of -40dB, specifically for X-band ~ -28dB. I won’t patronise you with what a thickness of 1cm would mean.
Also, you need to note that the T-50’s cowlings are not true cylinders – they are flared, in fact for the region in question are much closer to what in geometric terminology are known as ‘ogives’. Added to that, a complex ogive would mean the worst offending beam aspect region will only be a certain segment of the cowling, but not the length and arc of the cowling in its entirety.
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You can see for yourself that @ 9GHz and azimuth angle 90°, the measurement is around -15dB. As per NPO Saturn & Lyulka’s very own study into a metallic cone-cylinder model, the worst offending region is aspect/degree +/- 70° with 0dB (1m^2). Both these sources certainly contradict your insanely high baseline figure of 3m^2 (>5dB) akin to the average RCS of an untreated MiG-21 or F-18- just for the T-50’s side aspect!! This is a joke, right?!
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Factor in the 5mm of their CNT RAM and it is self-evident from both tables above that F-35 stealth levels will be achieved. One cm will probably take them to near F-22 levels. Having said that, I do concede the pole model pic does indeed show a banked section joining with the cowling. This is most probably indicative of the “significant structural changes” to the upcoming ‘Stage 2’ prototypes.
Either way, the notion that the current T-50s’ design ‘flaws’ from yours (and others’) physical optics analyses will somehow not be addressed- is itself flawed and simply not tenable.
…and that 3 years of development of that exact material has increased its heat tolerance by 400%.
Oh, and I wouldn’t worry about high temperature composites, the document from where the RCS graph and pole model pics were taken is from Spring 2014, and it clearly states “high temperature polymeric materials”, notwithstanding such PMCs for in-service systems such as the ‘Bulava’ SLBM and ‘Angara’ SLV.
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