Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Various Aspect Ratios as Determined by Flight Tests at Supersonic Speeds

reportActive / Technical Report | Accession Number: ADA800546 | Open PDF

Abstract:

Tests on rocket-propelled bodies carrying wings of aspect ratios between 3.8 and 5.0 at various swept-back angles show that drag coefficient decreased as swept-back angle increased and that this decrease becomes more pronounced with larger aspect ratios. For Mach numbers greater than value at which Mach line lies ahead of leading edge, drag coefficient decreased with decrease in aspect ratio. Aspect ratio effect diminished with increased swept-back angle. At 45 degrees only negligible drag coefficient changes resulted between aspect ratios of 1.5 and 5.0. Data substantiate theoretical calculations.

Author(s):
Tucker, Warren A. ; Nelson, Robert L.
Author Organization(s):
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
Descriptive Note:
Research memo.
Pagination:
0025

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
NACA-RM-L7C05
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_5_Command and Control; JCA_6_Net Centric
Modernization Areas:
Directed Energy
Communities of Interest:
Weapons Technologies
Descriptor(s):
*ASPECT RATIO, AIRFOILS, AERODYNAMIC CHARACTERISTICS
Keyword(s):
ATI 004858, ATI COLLECTION
Report Date:
1947 Apr 22
Creation Date:
2009 May 27