Inviscid transonic flow past forebodies of axisymmetric flight vehicles has been calculated. The method employs the basic feature of Carlson's relaxation method using cylindrical coordinates for the transonic full potential equation. The calculated flow characteristics are presented through the curves of pressure coefficient.
The physical properties of transonic flow over forebodies such as cone, ellipsoid and ogive are investigated. And the mutual interference between the forebodies and flares in staged launch vehicles is quantitatively analyzed. Comparison of the calculated data with the experimental results reported earlier shows good agreement.