It's a DAT file with the extension changed to make it acceptable to the bulletin board.
Airfoil generator 23012 generator#
Since Xfoil is no longer being developed and Profili is essentially a user friendly shell for modelers with some functionality for rib layout and foam CNC cutters I don't expect the NACA section generator to be a priority item.īTW for anybody who doesn't have the correctly drawn, reflexed, NACA 23112 here it is. Have you tried generating an NACA 6 digit section? Each 6 digit can be 4 different airfoils depending on whether the third place is occupied by an "A" or a "-" and mean line "1" or "0". Granted that would be 1/2% and the polars are so close it's probably within normal building tolerances for a homebuilder, but still it's a valid number in the sequence. Since the original description of the 5 digit naming convention clearly states that the second and third digits should describe twice the of camber, and computers are dumb, what do you do, add "unless the third digit is a 1"? What if somebody wants a 23112 with a strait line on the aft part. When I first heard about "1" in the third place designating a reflexed mean line I thought it was a dumb idea because it would lead to this. I'm using the registered version of Profili which I assume is using the Xfoil NACA section generator rather than writing a new one. The only original data on the 231xx that I know of is NACA-tr-537 He just added a little more reflex to the 23112 so that the mean line reverses direction at 75%c. This is what he said he used on the Pioneer I & II and it is not a hybrid with the 43012 as the UIUC database has it. I got the 23112-75 out of Jim Marske's book. The correct v labeled “Nacag 123 12.0 140 pts.”Īnd a more heavily reflexed v labeled “marske-23112-75” The section from post #4 labeled “hba 23112” I've included the NACA 23012 for reference and because the (1) in the third place in the 23()xx simply means it's a reflexed version. Type 2 polars conform to the relationship Re x Cl^0.5 = constant which should more accurately reflect the speed vs AoA of an actual flight. Attached is the L/D & Cm part of a type 2 polar generated by Profili. First the file in post #4 apparently is not the original 23112, it has a tiny bit more camber than what I now believe to be the real thing. I don't wish to dredge up a zombie thread but in the interest of completeness and accuracy I'm adding this so that the next person to look for this obscure old airfoil section can find it and some of it's derivatives more easily. Yes, the stall can be relatively sharp but with a conservative wing twist or light wing loading, most of the airplanes that used this section seemed to have avoided this characteritic. As such, the section performs relatively well not only in cruise but also in climb.Īlso, the section's relatively large leading edge radius and thick nose allows it to achieve a fairly high aoa, making it quite effective with a variety of flap cofigurations. The section also has a fairly low drag count and the bottom of the drag curve extends over a fairly long range of lift coefficients. This characteristic also allows for a more effective horizontal, resulting is a slightly larger allowable CG envelope for any given tail volume coefficient. First, it has a very low pitching moment and as such, its use results in relatively low amounts of trim drag. There are several reasons for its popularity. The applications include Aero Commanders, several of the single engine Cessnas, the Cessna Citation family, virtually all the Beech aircraft, several of the Douglas airliners, and on our end, pretty much all the Van's aircraft, to name a few.
Airfoil generator 23012 series#
The interesting thing about the 23000 series of airfoils is that in spite of the section data, the family has been used on a whole range of different airplanes.