Tabulation of data from tests of an NPL 9510 airfoil in the Langley 0.3-meter transonic cryogenic tunnel

Author:: Jenkins, R. V.
Published:: Nov 1, 1983.
Physical Description:: 1 electronic document

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Summary:

The tabulated data from tests of a six inch chord NPL 9510 airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel. The tests were performed over the following range of conditions: Mach numbers of 0.35 to 0.82, total temperature of 94 K to 300 K, total pressure of 1.20 to 5.81 atm, Reynolds number based on chord of 1.34 x 10 to the 6th to 48.23 x 10 to the 6th, and angle of attack of 0 deg to 6 deg. The NPL 9510 airfoil was observed to have decreasing drag coefficient up to the highest test Reynolds number.

Other Subject(s):

AERODYNAMICS

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 19840005083.
Accession ID: 84N13151.
NASA-TM-84579.
NAS 1.15:84579.

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