As a further contribution to the understanding of the effects of test-flow non-uniformities on the hypersonic flow over test bodies, the hypersonic small disturbance theory is used to investigate the flow over those slender plane and axisymmetric ogives that will support plane and conical shocks when immersed in line and point hypersonic source flows respectively. The results are compared with those obtained by zero-order Newtonian theory, and Van Dyke's small disturbance uniform flow results for the slender plane and axisymmetric ogives are used to assess the source flow effects . The source flow effect on the surface pressure is found to he particularly large.