Information on Boeing 747 Wing
Information on Boeing 747 Wing
(OP)
I posted a thread in a different area with two questions. I got a couple of replies to the first part, but no replies to the second part so I'll start a new thread around the second question here. I am trying to find out data on the Boeing 747 wing, specifically the airfoil and the L/D curves for it in order to approximately calculate the Lift and drag of the wing (for a 10th grade science fair.) I found on a website that the B-747 has an airfoil of "BAC 463 thru 468". What does that mean? Does the wing have varying airfoils from root to tip? What does a BAC 463, 464, 465, 466, 467, 468 look like? What do the L/D curves look like? Other, simpler airplanes use NACA 4 digit or 5 digit airfoils and I can look up the graphs of their LD curves, but I have no idea how to look up Boeing L vs AoA or D vs AoA curves.





RE: Information on Boeing 747 Wing
maybe you could turn the project around, and reverse engineer the aerodynamic properties based on a flight simulator ?
bare in mind the comments on the previous thread about compressibility effects.
possibly you could get more information on an out of production airplane (say B707, DC8, DC10).
good luck
RE: Information on Boeing 747 Wing
Not sure how the FAA certifies airplanes, but I would have thought that they'd file drawings with the Gov't somewhere, that something as basic as the airfoil shape wouldn't be kept secret, do they usually put patents on an airfoil shape? I thought airfoils were generated by a formula.
RE: Information on Boeing 747 Wing
i don't think the profile is patented, tho' there might be some design feature in the profile that is unique. you're right rpofiles are generated by a formulae, and that's the secret ! NACA (the precursor to NASA) has a bunch of profiles and L/D and CL data that are available to the public, but the trouble is relating these to the profiles Boeing used.
RE: Information on Boeing 747 Wing
Even if not that, then if there was some way of getting the Boeing L and D graphs for analysis would be sufficient.
RE: Information on Boeing 747 Wing
htt
And yes, airfoils change from root to tip.
Wes C.
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RE: Information on Boeing 747 Wing
RE: Information on Boeing 747 Wing
eg ... for stall performance, say your three sections are the same profile but with twist, maybe the tip has lower incidence than the root, maybe the incidence of the tip is equal to the plane's incidence, at the mid-span it might be +1 degree, at the root +2 degree. Thus when the root CL is maximum (stall) the CL at the other two sections can be determined. each section will have a portion of the wing area, this is how to average the three sections together,; so now you'll have the combined wing CL*S.
then Vstall = sqrt((1.1*Wt)*2/(rho*CL*S))
and this is flaps up
RE: Information on Boeing 747 Wing
It may be difficult to actually get the correct surface area for each "Zone" of respective airfoil/CL, but I could probably get an approximation by finding the distance out from the Centerline for each zone,(remember, the reference surface area usually used is the total "Wetted" area, including the extension into the fuselage profile--not just from the wing root outwards), finding what proportion that distance is to the total span and dividing the total area by that fraction. Find the respective Y distance for each zone to get a fraction of total span and multiply that fraction of total Area to get each respective area.
RE: Information on Boeing 747 Wing
as for your (CLi*Si) ... yeah, I'd associate a nominal area for each section, maybe 20% for the tip, 50% for the mid section and 30% for the root. maybe play with the %ages to see how much difference there is.
RE: Information on Boeing 747 Wing
http://www.ae.uiuc.edu/m-selig/ads/aircraft.html
Steven Fahey, CET
RE: Information on Boeing 747 Wing