Answers must contain an explanation using engineering logic, and assertions of fact must be supported by links to credible sources.īe substantive. Racism, sexism, or any other form of bigotry will not be tolerated.ĭon't answer if you aren't knowledgeable. All users are expected to behave with courtesy. From the results of thin airfoil theory, calculate the lift coefficient and the moment coefficient about the leading edge. Mechanical, Electrical, Civil, Chemical, and Computer are reserved for technical questions only.Ĭareer must be used for all questions on career advice, salary, job market, etc.ĭiscussion can be used for general questions that apply to multiple disciplines, including some workplace topics.īe respectful to other users. This profile was chosen as it is near this thickness that maximum lift coefficient is obtained. In real life, there are significant differences between a flat bottomed airfoil, semi symmetric airfoil and symmetric airfoils I have significant flying. Remember to flair your post.Īvoid questions that can easily be answered by searching on the internet. The airfoil chosen for the present work was NACA 0015 (symmetric and having a maximum thickness of 15). Post titles must be a question about engineering and provide context - be specific. Call for Engineers: Tell us about your job! (2020) New to AskEngineers? Read our subreddit rules and FAQ page before posting! Topic Filters ⇨ Exclude All Career Posts