HumanPoweredDesigner
Well-Known Member
http://airfoils.worldofkrauss.com/foils/1569
Just browse a while. You'll see they stall anywhere from -0.5 degrees up to 12 degrees, with 6 or 7 being the most common.
Yet I read many places that most thin airfoils stall at 15 degrees. And pilots on here say their props stall round 18 degrees.
Is the data base wrong? I developed a lot of my understanding of aerodynamics by looking at all the foils and picking out patterns, and checking those patterns against the characteristics of other airfoils in the database.
And Dae 31 from the Daedalus is said in some paper to have an L/D of 89 and Cl max of 1.9. Yet in this database, it is about 40 and 0.6. I know it probably has something to do with Reynolds number and scale size and speed. But the stall angle should be less variable.
Just browse a while. You'll see they stall anywhere from -0.5 degrees up to 12 degrees, with 6 or 7 being the most common.
Yet I read many places that most thin airfoils stall at 15 degrees. And pilots on here say their props stall round 18 degrees.
Is the data base wrong? I developed a lot of my understanding of aerodynamics by looking at all the foils and picking out patterns, and checking those patterns against the characteristics of other airfoils in the database.
And Dae 31 from the Daedalus is said in some paper to have an L/D of 89 and Cl max of 1.9. Yet in this database, it is about 40 and 0.6. I know it probably has something to do with Reynolds number and scale size and speed. But the stall angle should be less variable.
