A compilation of available experimental and analytical data is presented, dealing with the effects of propellers (and rotors) on V/STOL take-off and transition flight. Since the majority of the experimental work was conducted with small-scale propellers/rotors, considerable effort was expended to demonstrate the applicability of these data to full-scale propellers. The dependence of take-off performance on blade Reynold's number and tip Mach number is described. Recent results from the Navy flying wind tunnel have conclusively indicated the dependence of model V/STOL transition flight data on the character of the model test facility. Therefore, the correlation of model vs. fullscale propeller/rotor transition data was impossible because of the non-availability of accurate full-scale results. Data are presented describing identical tests run on the airship and in three different wind tunnels. A brief analytical treatment is described which might enable more work to proceed to correct for wall interference. In addition, the experimental techniques used to obtain accurate low velocity measurements and to obtain vibration-free straingage traces are briefly described. (Author).

An extremely practical overview of V/STOL (vertical/short takeoff and landing) aerodynamics, this volume offers a presentation of general theoretical and applied aerodynamic principles, covering propeller and helicopter rotor theory for both the static and forward flight cases. Both a text for students and a reference for professionals, the book can be used for advanced undergraduate or graduate courses. Numerous detailed figures, plus exercises. 1967 edition. Preface. Appendix. Index.

The report presents the reduced data obtained during an extensive series of propeller static performance tests which were run because of a static performance thrust deficiency encountered during flight tests of the XC-142A V/STOL Cargo Aircraft. Thirteen different propellers were used; 28 different configurations were obtained by changing parameters of some of the 13 blades. The reduced data for the 28 versions of propellers tested are presented. Parameters studied during the tests included blade cuff (on or off), tip shape, twist, activity factor, camber, and airfoil section. Data on several other static thrust propellers tested on Rigs Nos. 1 and 4, which were not a part of this test series, are also presented for additional information. The information obtained from the tests, in effect, represents a state-of-the-art study for improving propeller static performance for V/STOL aircraft applications. The information obtained during these tests can be used to more accurately predict static thrust for future propeller driven V/STOL aircraft. (Author).

The tests were made because of a static performance thrust deficiency encountered during flight tests of the XC-142A V/STOL cargo aircraft. Twenty-eight versions of propellers were tested. Parameters studied during the tests included blade cuff (on or off), tip shape, twist, activity factor, camber, and airfoil section. Reduced data are presented in the form of performance coefficients and various tip Mach numbers for each configuration tested. Data on several other VTOL static thrust propellers are presented for additional information although they were not a part of this test series. Complete blade characteristic charts describing the physical characteristics of each blade tested provide a means of comparing the distribution of twist, thickness, chord, and camber against blade redial location for any given blade. (Author).