THIN AIRFOILS IN HYPERSONIC FLOW WITH STRONG SHOCKS,
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 = f(x). 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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 19, 1957
- Accession Number
- AD0606545
Entities
People
- Joseph L. Raymond
Organizations
- RAND Corporation