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This is another paper that I presented to AIAA. This one is on delta wing lift and drag calculations.
You may notice that in the aerodynamics field, there is really no established complete theory on delta wings, although many airplanes have used the planform for amny years. The famouse ones are the Concord and the J-7 and J-8 fighters. If you have experimental data to check against my results, please do so.
Particularly missing is the evaluation on non-linear, or vortex lift. The only model that separates such force is the "Leading Edge Suction Analogy" method quoted in the paper. I also pointed out the falacy in that scheme.
On the linear lift and drag evaluation, traditional analysis utilizes the "Slendar Wing Theory". I am not cetain that that theory produce a correct results as the pure potential flow solution is very far off from the overall lift. In addition, the traditional analysis drag polar relationship also gives rediculous results.
As I mentioned before, I hope by presenting my viewpoints and new appraoches, I can inspire a movement within the Chinese fluid/aero experts to thouroughly investigate and clarify this entire field. |
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发表于 2006-9-15 06:53:57
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