A study of flow changes associated with airfoil section drag rise at supercritical speeds Page: 22 of 32
31 p.View a full description of this report.
- Highlighting
- Highlighting On/Off
- Color:
- Adjust Image
- Rotate Left
- Rotate Right
- Brightness, Contrast, etc. (Experimental)
- Cropping Tool
- Download Sizes
- Preview all sizes/dimensions or...
- Download Thumbnail
- Download Small
- Download Medium
- Download Large
- High Resolution Files
- IIIF Image JSON
- IIIF Image URL
- Accessibility
- View Extracted Text
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA TN No. 1813
Angle of attack, , deg
F/gure 5 -Variation of critical, drag-divergence, and shock-stall
Mach numbers with angle of attack for the NAGA 230/5
oirfoil 'section.21
Upcoming Pages
Here’s what’s next.
Search Inside
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Matching Search Results
View 14 places within this report that match your search.Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Nitzberg, Gerald E. & Crandall, Stewart. A study of flow changes associated with airfoil section drag rise at supercritical speeds, report, February 1949; (https://digital.library.unt.edu/ark:/67531/metadc55116/m1/22/?q=drag+rise: accessed May 27, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.