Aerodynamic Design Methodology for Air Propellers of Swarm UAVs under Variable Mission Payloads

Viacheslav Bezpalyy; Yevgen Ukrainets; Kostyantyn Myronenko; Vasyl Loginov

doi:10.2478/tar-2025-0013

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Aerodynamic Design Methodology for Air Propellers of Swarm UAVs under Variable Mission Payloads

Transactions on Aerospace Research

Volume 2025 (2025): Issue 3 (September 2025)

By: Viacheslav Bezpalyy , Yevgen Ukrainets , Kostyantyn Myronenko and Vasyl Loginov

Open Access

|Oct 2025

Figures & Tables

Circulation distribution along the AP blade.

Velocity distribution along the AP blade.

Inflow angle distribution along the AP blade.

Distribution of the power coefficient derivative β′ along the relative radius of the AP blade.

Distribution of the thrust coefficient derivative α′ along the relative radius of the AP blade.

Blade thickness distribution along the AP radius.

Distribution of the cross-section setting angle along the AP blade radius.

Mach number distribution along the AP blade radius.

Distribution of the optimal angles of attack along the AP blade radius.

Distribution of the optimal lift coefficients along the AP blade radius.

Table 1.

Experimental and Calculated Characteristics of the 3 SMV-1 Air Propeller.

Parameter	Parameter value
λ	0.90	1.00	1.10	1.20	1.30	1.40	1.50
α (experiment)	0.13617	0.1256	0.11096	0.09399	0.07591	0.05765	0.03997
α (calculation)	0.13523	0.11709	0.09832	0.07893	0.05896	0.03843	0.01735
β (experiment)	0.16649	0.157	0.14639	0.13402	0.11925	0.10144	0.07994
β (calculation)	0.14602	0.13547	0.12161	0.10428	0.08331	0.05856	0.02985
η (model experiment)	0.73614	0.8000	0.83378	0.84159	0.82751	0.79563	0.75006
η (calculation)	0.83347	0.86433	0.88931	0.90833	0.91999	0.91871	0.87224
Flight speed, km/h	285.1	316.8	348.5	380.2	411.8	443.5	475.2
Propeller thrust, kg (experiment)	1001.2	923.5	815.8	691.0	558.1	423.8	294.0
Propeller thrust, kg (calculation)	994.3	860.9	722.9	580.3	433.5	282.5	127.6
Power consumption, h.p. (experiment)	1436.3	1354.4	1262.9	1156.2	1028.7	875.1	689.6
Power consumption, h.p. (calculation)	1259.7	1168.7	1049.1	899.6	718.7	505.2	257.5

Table 2.

Known and Calculated Characteristics of the MTV-5-1/210 Air Propeller at φ_0.75 = 15°.

Parameter	Parameter value
λ	0.3	0.4	0.5	0.6
α	0.116	0.097	0.065	0.020
α (calculation)	0.123	0.091	0.069	0.044
β	0.074	0.064	0.050	0.033
β (calculation)	0.074	0.064	0.052	0.037
η	0.531	0.604	0.704	0.758
η (calculation)	0.480	0.604	0.650	0.620

Table 3.

Known and Calculated Characteristics of the Air Propeller MTV-5-1/210 at φ_0.75 = 20°.

Parameter	Parameter value
λ	0.3	0.4	0.5	0.6	0.7	0.8
α	0.195	0.171	0.143	0.111	0.074	0.033
α (calculation)	0.179	0.154	0.132	0.107	0.080	0.050
β	0.135	0.123	0.108	0.090	0.067	0.042
β (calculation)	0.138	0.128	0.115	0.099	0.079	0.054
η	0.417	0.517	0.614	0.697	0.760	0.789
η (calculation)	0.445	0.569	0.660	0.717	0.741	0.731

Table 4.

Known and Calculated Characteristics of the Air Propeller MTV-5-1/210 at φ_0.75 = 25°.

Parameter	Parameter value
λ	0.3	0.4	0.5	0.6	0.7	0.8	0.9	1.0	1.1
α	0.269	0.252	0.229	0.201	0.169	0.131	0.089	0.042	−0.010
α (calculation)	0.232	0.215	0.196	0.175	0.151	0.124	0.096	0.065	0.031
β	0.209	0.204	0.194	0.178	0.156	0.129	0.097	0.059	0.016
β (calculation)	0.213	0.205	0.194	0.180	0.163	0.141	0.115	0.083	0.047
η	0.351	0.449	0.540	0.621	0.692	0.753	0.802	0.831	0.792
η (calculation)	0.417	0.528	0.600	0.666	0.736	0.799	0.819	0.740	0.480

Table 5.

Known and Calculated Characteristics of the Air Propeller MTV-5-1/210 at φ_0.75 = 30°.

Parameter	Parameter value
λ	0.4	0.5	0.6	0.7	0.8	0.9	1.0	1.1	1.2	1.3
α	0.298	0.292	0.276	0.254	0.226	0.192	0.155	0.116	0.075	0.035
α (calculation)	0.270	0.255	0.238	0.218	0.196	0.172	0.145	0.117	0.087	0.055
β	0.285	0.289	0.283	0.268	0.247	0.221	0.189	0.152	0.108	0.056
β (calculation)	0.293	0.288	0.278	0.265	0.248	0.226	0.199	0.168	0.131	0.089
η	0.394	0.474	0.548	0.616	0.677	0.731	0.779	0.821	0.848	0.855
η (calculation)	0.448	0.530	0.603	0.669	0.729	0.780	0.820	0.843	0.842	0.809

Table 6.

Known and Calculated Characteristics of the Air Propeller MTV-5-1/210 at φ_0.75 = 35°.

Parameter	Parameter value
λ	0.6	0.7	0.8	0.9	1.0	1.1	1.2	1.3	1.4	1.5
α	0.336	0.327	0.310	0.286	0.256	0.223	0.188	0.151	0.111	0.067
α (calculation)	0.293	0.278	0.260	0.241	0.219	0.196	0.171	0.144	0.116	0.086
β	0.360	0.374	0.377	0.369	0.348	0.316	0.274	0.224	0.170	0.117
β (calculation)	0.384	0.378	0.367	0.352	0.333	0.309	0.279	0.245	0.205	0.159
η	0.489	0.550	0.606	0.658	0.705	0.749	0.786	0.820	0.847	0.865
η (calculation)	0.556	0.607	0.654	0.699	0.745	0.788	0.827	0.856	0.870	0.859

Table 7.

Known and Calculated Characteristics of the Air Propeller MTV-5-1/210 at φ_0.75 = 40°.

Parameter	Parameter value
λ	1.5	1.6	1.7	1.8	1.9	2.0
α	0.196	0.160	0.122	0.081	0.037	−0.009
α (calculation)	0.178	0.152	0.125	0.097	0.068	0.037
β	0.347	0.294	0.235	0.169	0.096	0.017
β (calculation)	0.353	0.312	0.267	0.216	0.159	0.097
η	0.809	0.834	0.853	0.856	0.863	0.818
η (calculation)	0.845	0.898	0.899	0.848	0.744	0.588

Table 8.

Results of the Verification Calculation for the AV-68 Air Propeller.

Parameter Name	Value of Calculated Parameters		Experiment
Advance ratio λ	0.7	0.8	0.742
Thrust coefficient α	0.1973	0.1746	0.186
Power coefficient α	0.2182	0.2022	0.2108
KPD η	0.6331	0.6907	0.655
Propeller thrust, kg	3240.5	2866.7	3070
Consumped power, h.p.	3848.3	3566.3	3720
Flight speed, km/h	203.0	232.0	215

A 3D model of the AP designed for a flight speed of 50 km/h (D=0.38 m; N=0.4 h.p.; 83,333 rps).

A 3D model of the AP designed for a flight speed of 120 km/h (D=0.38 m; N=0.6 h.p.; 100 rps).

A 3D model of the AP with a reduced blade chord.

Dependence of the AP efficiency on the relative flight speed: – . . – . . characteristic of the propeller with a reduced blade chord width; —— characteristic of the propeller with an increased blade chord width.

Dependence of the propeller thrust on the flight speed: – . . – . . characteristic of the AP with a reduced blade chord width; —— characteristic of the AP with an increased blade chord width. Source: Developed by the author.

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DOI: https://doi.org/10.2478/tar-2025-0013 | Journal eISSN: 2545-2835

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Language: English

Page range: 41 - 61

Submitted on: Aug 24, 2025

Accepted on: Oct 2, 2025

Published on: Oct 31, 2025

Published by: ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION

In partnership with: Paradigm Publishing Services

Keywords:

UAV,

Related subjects:

Introductions and overviews,

Materials sciences, other,

Physics,

Physics, other

© 2025 Viacheslav Bezpalyy, Yevgen Ukrainets, Kostyantyn Myronenko, Vasyl Loginov, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

Volume 2025 (2025): Issue 3 (September 2025)

Aerodynamic Design Methodology for Air Propellers of Swarm UAVs under Variable Mission Payloads

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Table 8.

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