Hi Peril, One of our members on the J-aicraft website gave me this thread and I am blown away. I continue to scour the net for data and books, the gaps are slowly getting filled and every week I learn something new and refine a bit more my skill and data levels with all different manner of aircraft.Ĩ Responses to “Japanese Airfoils, Tora Tora Tora!” We have resolved the A6M wing, the G4M wing, the Ki-44 wing and now the B5N wing, a few more exist yet but I am hopeful I can eventually get this information. OK, so now we have another wing airfoil gap filled, the B5N now has a wing I’m happy is very close to as it should be. BINGO □ The plots agreed with the naming convention we had discovered for the NN-5, it was a 2200 series foils with 2.5 camber, 16% chord thickness and 30% chord position. Lucky for me I had found the NN-2 data plots already and could referance the plots against the 2200 series with chord and camber changes. Reference to thickness at 30% also pointed to 2200 series airfoils being the base and i did some quick plotting in Profili to see how they looked. The listed the NN-5 2.5 16 and the NN-5 1.4 8 were seeming based on a 2200 series airfoil, the numbers listed seemed to indicate camber and chord data. The NN series (Nakijima Airfoil) had a number of clues which we found in the text associated with the diagrams. NACA 2200 series was American so the Japanese used their own naming convention instead, NN-X. Tora pointed out that at the time of these being designed, the Japanese did not like to refer to anything in it’s American name. Tora found a nice diagram of some NN series airfoils, with a loose descriptions referring to the NACA 2200 series. Japanese airfoil data is one of the hardest things to get a hold of, I have managed to track a number of airfoils and today we filled in another gap, the NN-5 Airfoil. I invited Tora to pop over for a translation session, we went over my data sets and he brought over a few Maru books we could search in for Airfoil data. I’m happier it’s an improvement with the changes and now very close to max speed specs at all alts. I went over the data for the Beaufighter VI and rebuilt the engine and props to match what I could find now. Sample profiles are already integrated in Mecaflux, you just have to choose your profile.Over the last week or so i have been revisiting some of the unknown information I have and trying to fill some data gaps. Curves, called polar, give you the coefficient of lift and drag, depending on the incidence (attack angle) of profile and the Reynolds number.Įxample Polar found in the databases of profiles data dat format available for download:ĭownload List profile coordinate ZIP file:Ĭoordinate files ( sample file, profile coordinate) allow to draw precisely the profiles. Which profiles are used to which aircraft ?.You will find the links below, the data in tables that can be inserted in the profile editor mecaflux to calculate their lift and drag: In these databases you will find all the information necessary to know the characteristics of a given profile. Hundreds of profiles have been tested in the wind tunnel. One of the most famous is the NACA airfoil database. The wind tunnel test results are available in databases.
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