In reality, the boundary layer on the airfoil discussed in Prob. 5.37 is neither fully laminar nor fully turbulent. The boundary layer starts out as laminar, and then transitions to turbulent at some point downstream of the leading edge (see the discussion in Sec. 4.19.) Assume that the critical Reynolds number for transition is 650,000. Calculate the skin friction drag coefficient on the NACA 2415 airfoil, and compare your result with the experimental section drag coefficient in App. D. Note: You will find from the answer to this problem that 86 percent of the airfoil section drag coefficient is due to skin friction and 14 percent due to pressure drag from :flow separation. Comparing this answer with the result of Prob. 5.36, which pertains to a thinner airfoil, we find that the pressure drag is a higher percentage for the thicker airfoil. However, for airfoils in general, the pressure drag is still a small percentage of the total drag. This drag breakdown is somewhat typical for airfoils at small angles of attack. By intent, the streamlined shape of airfoils results in small pressure drag, typically on the order of 15 percent of the total drag. Prob. 5.37 Here we continue in the vein of Probs. 5.34-5.36, except we examine a thicker airfoil and look at the relative percentages of skin friction and pressure drag for a thicker airfoil. Estimate the skin friction drag coefficient for the NACA 2415 airfoil in low-speed incompressible :flow at Re = 9 x 106 and zero angle of attack for (a) a laminar boundary layer, and (b) a turbulent boundary layer. Compare the results with the experimentally measured section drag coefficient given in App. D for the NACA 2415 airfoil. What does this tell you about the relative percentages of pressure drag and skin friction drag on the airfoil for each case? Probs. 5.34 Consider an NACA 2412 airfoil in a low-speed :flow at zero degrees angle of attack and a Reynolds numberof8.9 x 106. Calculate the percentage of drag from pressure drag due to :flow separation (form drag). Assume a fully turbulent boundary layer over the airfoil. Assume that the airfoil is thin enough that the skin-friction drag can be estimated by the :flat-plate results discussed in Ch. 4. Probs. -5.36 Returning to the conditions of Problem 5.34, where the boundary layer was assumed to be fully turbulent, let us now consider the real situation where the boundary layer starts out as laminar, and then makes a transition to turbulent somewhere downstream of the leading edge. Assume a transition Reynolds number of 500,000. For this case, calculate the percentage of drag that is due to :flow separation (form drag).

**. WITH BEST NURSING TUTORS TODAY AND GET AN AMAZING DISCOUNT **

The post Calculate the skin friction drag coefficient on the NACA 2415 airfoil, and compare your result with the experimental section drag coefficient in App. appeared first on BEST NURSING TUTORS .

Use Discount Code “Newclient” for a 15% Discount!

NB: We do not resell papers. Upon ordering, we do an original paper exclusively for you.

The post Calculate the skin friction drag coefficient on the NACA 2415 airfoil, and compare your result with the experimental section drag coefficient in App. appeared first on The Nursing TermPaper.

Calculate the skin friction drag coefficient on the NACA 2415 airfoil, and compare your result with the experimental section drag coefficient in App. was first posted on October 11, 2020 at 5:44 am.

©2019 "Essay Lords | Bringing Excellence to students world wide". Use of this feed is for personal non-commercial use only. If you are not reading this article in your feed reader, then the site is guilty of copyright infringement. Please contact me at support@essaylords.us

Basic Guarantees

- Free title page and bibliography
- Free unlimited revisions
- Plagiarism-free papers
- Money-back guarantee
- 24/7 support

On-demand options

- Writer’s samples
- Progressive delivery
- Plagiarism report
- Copies of used sources
- Expert Proofreading

Paper format

- 275 words per page
- 12 pt Arial/Times New Roman
- Double or single line spacing
- Any citation style (APA, MLA, Chicago/Turabian, Harvard)

Writing quality papers is a TOP priority. One expert takes one order at a time.

The service package includes topic brainstorm, research, drafting, proofreading, plagiarism check, citation formatting, and revisions.

We appreciate how valuable your time is. Hence, we make sure all custom papers are 100% original and delivered within the agreed time frame

Read moreEach paper is written from scratch, according to your instructions. It is then checked by our plagiarism-detection software. There is no gap where plagiarism could squeeze in.

Read moreWe see it as our duty to follow all instruction the client provides. If you feel the completed paper does not meet your exact requirements, we will revise the paper if you let us know about the problem within 14 business days from the date of delivery.

Read moreYour email is safe, we use your personal data for legal purposes only and in accordance with personal data protection law. Your payment details are also secure, as we use only reliable payment systems.

Read moreYou can easily contact us with any question or issues you need to be addressed. Also, you have the opportunity to communicate directly with assigned writer, e-mail us, submit revision requests, chat with us online, or call our toll-free on our site. We are always available to our customers.

Read more
The price is based on these factors:

Academic level

Number of pages

Urgency