Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Aspect Ratios of 1.5 and 2.7 as determined by Flight Tests at Supersonic Speeds

Alexander, Sidney R.; Katz, Ellis

Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Aspect Ratios of 1.5 and 2.7 as determined by Flight Tests at Supersonic Speeds

Active / Technical Report | Accession Number: ADA801409 |

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Abstract:

Data was obtained by tracking rocket-propelled bodies carrying wings of various plan forms. Results showed that for investigations in Mach number range of 1.05 - 1.35, an increasing swept-back angle and decreasing aspect ratio reduced the value of wing drag coefficient. Decreasing the aspect ratio always decreased the wing drag coefficient although, this effect was observed to become very small at higher swept-back angles.

Author(s):

Alexander, Sidney R. ; Katz, Ellis

Author Organization(s):

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY

Descriptive Note:

Research memo.

Pagination:

0023

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-L6J16

Monitor Series:

NACA

Subject Terms

Joint Capability Areas:

JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means

Communities of Interest:

Weapons Technologies

Descriptor(s):

*SWEPTBACK WINGS, FLIGHT TESTING, AIRFOILS, COEFFICIENTS, DRAG, WINGS, SUPERSONIC CHARACTERISTICS, ASPECT RATIO, ANGLES, MACH NUMBER

Keyword(s):

ATI 10442, ATI COLLECTION

Report Date:

1947 Feb 24

Creation Date:

2011 Aug 10