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An investigation was made in the Langley gust tunnel of a 60 degree sweptback-wing model to determine its response to gusts. On the basis of results, a simplified method of analysis, which uses a slope of the lift curve derived by the cosine law and which uses strip theory to estimate the penetration effect, appears to be applicable for the prediction of gust loads on wings swept as much as 60 degrees.
An investigation was made in the Langley gust tunnel of a flexible-wing model with the semichord line swept back 45 degrees to obtain experimental data on the amount of gust-load alleviation that might be expected as a result of the wings flexing under load. The results indicated that unless adverse pitching motion could be eliminated or reduced the over-all load reduction would be small. The net reduction in bending moment, however, may be appreciable.