So, in terms of a "nominal altitude": most commercial aircraft cruise at approximately 35,000 ft., but this is more to do with engine efficiency (more as well, but I digress). Do you think I made any mistake so far? How should I continue at step 3? This is my current situation thanks to the different comments:Ģ) listed my constraints and determined Cl: ģ) tried to look up a 4-digit airfoil on : I found some good basic explanation in the comments here: īut the author unfortunately skips some steps. I do understand that picking the optimal airfoil may be an iterative procedure but already a first approximation or something would be fantastic. The database I am using to look up some airfoils is really huge ( ) so it is difficult to make a proper choice.īut it would be interesting if someone could show and/or explain using a realistic scenario what steps he would go through in order to pick the airfoil that is suited for him. Long story short, I am interested in knowing how to choose the correct NACA airfoil. I suppose choosing one from a catalogue is way easier than custom designing one yourself. Issue is that they never really show how people picked the correct airfoil in the past, in stead they explain the different parameter of airfoils. The book I am reading (see title above) says on page 40, that engineers in the past used to select the appropriate airfoil from a catalog and that nowadays they go for custom-design. Issue with the answers I found online is that it doesn't really contain the information I am looking for. ![]() Now, the question in the title has already been asked a zillion times online as far as I can see. I am learning more about aerodynamics and aircraft configuration by reading various books like i.a.: "Aircraft design - a conceptual approach" by Raymer
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