Accession Number:

AD0606545

Title:

THIN AIRFOILS IN HYPERSONIC FLOW WITH STRONG SHOCKS,

Descriptive Note:

Corporate Author:

RAND CORP SANTA MONICA CALIF

Personal Author(s):

Report Date:

1957-12-19

Pagination or Media Count:

26.0

Abstract:

The expression for normal force is derived in closed form for the case of hypersonic flow with strong shocks, a logical extension of the isentropic case carried out by Dorrance and by Linnell in the regime 0.1 or K or 10. The method is especially useful in applications to convex airfoils with continually varying slope whenever the profile can arbitrarily be defined as y fx. In this case the closed form solution eliminates the piecemeal tangent-wedge type of approximation which is inherently laborious and limited in accuracy. The expression is derived from a simple relation between the two-dimensional pressure coefficients for shocks and expansion flows. Although this relationship is based on small-disturbance theory the force calculations appear to agree with exact shock-expansion theory and with experiment to angles of attack of 25 degrees, hence is anomalous to a certain extent. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE