1. Wyznaczanie podstawowych osiągów samolotu

Obliczam wskaźnik obciążenia mocy q_N według wzoru:

$$q_{N} = \frac{m_{\max}}{N_{\max}} = \frac{758\ kg}{70,56kW} = 10,74$$

m_max = 758kg

N_max = 70, 56 kW

1. Metoda mocy i przykładowe obliczenia

-Prędkość lotu (dla h=0m)

$$V = \sqrt{\frac{2 \bullet m \bullet g}{\rho \bullet S} \bullet \frac{1}{C_{z}}}$$

$$V = \sqrt{\frac{2 \bullet 758 \bullet 9,81}{1,225 \bullet 11,59} \bullet \frac{1}{1,294}} = 28,44\ m/s$$

-Moc niezbędna dla lotu poziomego

$$N_{n} = m \bullet g \bullet \sqrt{\frac{2 \bullet m \bullet g}{\rho \bullet S \bullet E}}$$

$$N_{n} = 758 \bullet 9,81 \bullet \sqrt{\frac{2 \bullet 758 \bullet 9,81}{1,225 \bullet 11,59 \bullet 206,224}} = 16755,38\ W$$

-Prędkość wznoszenia samolotu

$$w = \frac{N}{m \bullet g}$$

$$w = \frac{29444,2}{758 \bullet 9,81} = 3,95\ m/s$$

-Kąt wznoszenia

$$\gamma = \text{arc\ sin}\frac{w}{V}\ \lbrack\ rad\rbrack$$

$$\gamma = \text{arc\ sin}\left( \frac{3,95}{28,442} \right) \bullet \left( \frac{180^{0}}{\pi} \right) = {8,002}^{0}$$

h=0m; $\rho = 1,2255\ \frac{\text{kg}}{m^{3}}$

LP	Cz zakł	E	V	Nn obl	Nr	delta N	W obl	gamma obl	stopnie
1	1.294	206.224	28.44214	16755.38	46200	29444.62	3.959749	0.139675	8.002784
2	0.634	135.088	40.63792	20702.13	57120	36417.87	4.897521	0.12081	6.921884
3	0.386	56.507	52.06494	32009.15	63840	31830.85	4.280654	0.08231	4.716044
4	0.263	23.030	63.05236	50139.32	68880	18740.68	2.52027	0.039982	2.290784

h=1000m; $\rho = 1,1120\ \frac{\text{kg}}{m^{3}}$

LP	Cz zakł	E	V	Nn obl	Nr	delta N	W obl	gamma obl	stopnie
1	1.294	206.224	29.85817	17589.57	39669.88	22080.31	2.969388	0.099614	5.707487
2	0.695	151.728	40.76117	20506.49	49400.23	28893.73	3.885666	0.095473	5.470177
3	0.510	96.590	47.56217	25701.46	55388.13	29686.67	3.992302	0.084037	4.814992
4	0.326	38.619	59.46506	40646.77	60627.55	19980.78	2.687041	0.045202	2.5899
5	0.263	23.030	66.1915	52635.57	62873.02	10237.45	1.376745	0.020801	1.191805

h=2500m; $\rho = 0,957074\ \frac{\text{kg}}{m^{3}}$

LP	Cz zakł	E	V	Nn obl	Nr	delta N	W obl	gamma obl	stopnie
1	1.445	209.428	30.4642	18814.4	34294.85	15480.44	2.08183	0.06839	3.918471
2	0.864	179.011	39.40229	20350.2	43647.98	23297.79	3.133116	0.0796	4.560751
3	0.510	96.590	51.26781	27703.9	49259.87	21555.97	2.898874	0.056574	3.241447
4	0.386	56.507	58.91548	36220.8	51754.04	15533.24	2.088929	0.035464	2.031926
5	0.326	38.619	64.09807	43813.62	52377.58	8563.961	1.151692	0.017969	1.029526

h=4000m; $\rho\ = 0,8192\ \frac{\text{kg}}{m^{3}}$

LP	Cz zakł	E	V	Nn obl	Nr	delta N	W obl	gamma obl	stopnie
1	1.777	210.432	29.68553	20287.56	28692.92	8405.361	1.130364	0.038087	2.182232
2	0.960	188.019	40.39441	21462.7	36378.52	14915.82	2.005898	0.049678	2.846354
3	0.634	135.088	49.70421	25320.76	39965.14	14644.37	1.969394	0.039633	2.270783
4	0.386	56.507	63.68059	39150.36	42527	3376.643	0.454095	0.007131	0.40857
5	0.326	38.619	69.28236	47357.29	43039.38	-4317.91	-0.58068	-0.00838	-0.48022

h=5000m; $\rho = 0,7361\ \frac{\text{kg}}{m^{3}}$

LP	Cz zakł	E	V	Nn obl	Nr	delta N	W obl	gamma obl	stopnie
1	1.777	210.432	31.31637	21402.1	25386.33	3984.229	0.535804	0.01711	0.980344
2	1.048	202.603	40.78524	21811.66	31621.56	9809.9	1.319248	0.032352	1.853624
3	0.695	151.728	50.09958	25204.54	35184.56	9980.018	1.342125	0.026792	1.535089
4	0.510	96.590	58.45869	31589.67	36520.68	4931.007	0.663128	0.011344	0.649951
5	0.386	56.507	67.17902	41301.17	36966.05	-4335.11	-0.58299	-0.00868	-0.49723

h [m]	Vmin [km/h]	Vmax [km/h]	W max [m/s]	Vw [km/h]	Gamma max [*]	Vgamma [km/h]
0	102.4	227.0	4.9	146.3	8.0	102.4
1000	107.5	234.7	4.0	171.2	5.7	107.5
2500	109.7	230.7	3.1	141.8	4.6	141.8
4000	106.8	249.4	2.0	145.4	2.8	145.4
5000	113.1	241.8	1.34	180.3	1.85	146.8