Studies In Supersonic Aerodynamics As Applied To Controlled Flight
Abstract
Measurements have been made on specially streamlined 5-inch rocket missiles in free flight at velocities from 1.85 to 0.9 times the velocity of sound. Ground observation techniques, for supersonic missiles including photo- triangulation, are discussed. Frequency deviation of a high frequency (60 megacycle) carrier has been used for telemetering pressures and accelerations in free flight. Drag measurements using sondes are found to be in good agreement with predictions of drag for simple bodies. The net drag coefficient, referred to a given body cross section area was 0.81 at Mach No. 1.6 for the streamlined missile. Measurements of base pressure check the von Karman-Moore values for base drag; the coefficient is about 0.20 at Mach No. 1.6. Pressure surveys on GU-2 aerofoils indicate fair agreement with linear flow theory and with the exact theory of Lighthill-Murnaghan at Mach numbers for which the latter theory is valid. These pressure measurements indicate the need for new theory in the transonic regime, Mach No. 1.5 to 1.0, for 10 per cent GU-2 aerofoils. A flip wing assembly using a delay squib has been built which introduces angles of incidence on two wings at pre-selected times of flight. This assembly, by causing angular acceleration, allowed determination of coefficients of lift for GU-2, i.e. double convex, aerofoils.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1946
- Accession Number
- AD0634868
Entities
People
- Robert P. Petersen
Organizations
- Johns Hopkins University