1 / 11

Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok

ORION AEROSPACE. Aerodynamics Preliminary Design Review #1 October 3, 2000. Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok. ORION AEROSPACE. Aircraft Geometry – 3-View. ORION AEROSPACE. Aircraft Geometry. Airfoil selection process

waite
Download Presentation

Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. ORION AEROSPACE Aerodynamics Preliminary Design Review #1 October 3, 2000 Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok

  2. ORION AEROSPACE Aircraft Geometry – 3-View

  3. ORION AEROSPACE Aircraft Geometry • Airfoil selection process • Gather data on various airfoils • Run data thru xfoil • Compare xfoil to experimental data (www.nasg.com) • -Airfoil section • Wing: Selig Donovan 7062 • Vertical tail: flat plate assumption • Horizontal tail: flat plate assumption

  4. ORION AEROSPACE Aircraft Geometry

  5. ORION AEROSPACE Aircraft Geometry

  6. ORION AEROSPACE Airfoil Data – S/D 7062

  7. ORION AEROSPACE

  8. ORION AEROSPACE Aircraft Geometry

  9. ORION AEROSPACE Aircraft Geometry • Aircraft wetted area: 59.5 ft2 • Wing – 38.70 ft2 • Struts - .83 ft2 • Tails – 9.01 ft2 • Landing gear - .003 ft2 • Aspect ratio of wing: 2.2

  10. ORION AEROSPACE Aerodynamic Mathematical Model • Lift Coefficient - CL=Clalpha*(alpha-alpha0lift) -Drag Coefficient - CDo=Cdwing+Cdfuselage+Cdvtail+Cdhtail+CdLg+CdStrut CDi=(CL^2)/(pi*AR*e) CD=CDo+CDi -Clmax - 2D: 1.53 - 3D: 1.22

  11. ORION AEROSPACE Questions?

More Related