5.5x4.7E (55x47E.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.5000 4.7000 0.0000 0.0000 0.2500 0.0000 0.1343 0.0000 0.0672 0.0000 0.0750 0.0000 0.0000 0.0726 0.4782 4.7000 0.0128 -0.2175 0.2465 0.0087 0.1320 1.6048 0.0631 0.0811 0.0817 0.0065 -0.0177 0.1452 0.4590 4.7000 0.0987 -0.4064 0.2432 0.0322 0.1298 6.1759 0.0596 0.0829 0.0985 0.0142 -0.0105 0.2178 0.4474 4.7000 0.3191 -0.4546 0.2403 0.0662 0.1277 13.1270 0.0571 0.0804 0.1204 0.0221 0.0012 0.2904 0.4483 4.7000 0.7173 -0.2668 0.2378 0.1069 0.1257 21.4605 0.0563 0.0747 0.1467 0.0299 0.0163 0.3630 0.4631 4.7000 1.3089 0.2152 0.2358 0.1505 0.1238 29.8498 0.0573 0.0672 0.1768 0.0369 0.0338 0.4356 0.4890 4.7000 2.0704 0.9966 0.2343 0.1933 0.1220 37.1060 0.0597 0.0588 0.2087 0.0429 0.0527 0.5082 0.5199 4.7000 2.9297 2.0112 0.2334 0.2313 0.1204 42.5363 0.0626 0.0504 0.2395 0.0475 0.0719 0.5808 0.5485 4.7000 3.7638 3.0850 0.2333 0.2610 0.1188 45.8851 0.0652 0.0425 0.2649 0.0503 0.0899 0.6534 0.5681 4.7000 4.4110 3.9689 0.2338 0.2783 0.1174 47.0548 0.0667 0.0357 0.2807 0.0508 0.1051 0.7260 0.5739 4.7000 4.6974 4.4516 0.2352 0.2795 0.1160 45.8402 0.0666 0.0303 0.2817 0.0480 0.1146 0.7981 0.5690 4.7000 4.7000 4.5870 0.2368 0.2690 0.1148 43.1460 0.0653 0.0264 0.2715 0.0431 0.1181 0.8611 0.5636 4.7000 4.7000 4.6543 0.2378 0.2583 0.1138 40.9789 0.0641 0.0242 0.2613 0.0397 0.1175 0.9237 0.5578 4.7000 4.7000 4.6772 0.2384 0.2460 0.1128 39.0013 0.0629 0.0234 0.2499 0.0362 0.1128 0.9862 0.5516 4.7000 4.7000 4.6669 0.2385 0.2321 0.1117 37.1789 0.0616 0.0235 0.2374 0.0328 0.1046 1.0488 0.5451 4.7000 4.7000 4.6514 0.2383 0.2171 0.1107 35.4975 0.0603 0.0237 0.2243 0.0294 0.0948 1.1113 0.5381 4.7000 4.7000 4.6310 0.2377 0.2024 0.1097 33.9439 0.0590 0.0238 0.2114 0.0264 0.0849 1.1739 0.5308 4.7000 4.7000 4.6118 0.2367 0.1883 0.1086 32.5062 0.0577 0.0236 0.1987 0.0239 0.0756 1.2364 0.5230 4.7000 4.7000 4.5983 0.2353 0.1749 0.1076 31.1734 0.0563 0.0231 0.1863 0.0221 0.0675 1.2990 0.5148 4.7000 4.7000 4.5923 0.2336 0.1623 0.1066 29.9357 0.0549 0.0224 0.1742 0.0210 0.0607 1.3615 0.5063 4.7000 4.7000 4.5906 0.2315 0.1503 0.1056 28.7844 0.0534 0.0215 0.1624 0.0204 0.0545 1.4241 0.4973 4.7000 4.7000 4.5889 0.2290 0.1386 0.1045 27.7116 0.0520 0.0206 0.1509 0.0198 0.0483 1.4866 0.4880 4.7000 4.7000 4.5872 0.2262 0.1272 0.1035 26.7102 0.0505 0.0196 0.1396 0.0193 0.0422 1.5492 0.4782 4.7000 4.7000 4.5855 0.2230 0.1161 0.1025 25.7738 0.0490 0.0187 0.1286 0.0188 0.0360 1.6117 0.4680 4.7000 4.7000 4.5838 0.2195 0.1053 0.1015 24.8968 0.0475 0.0178 0.1178 0.0184 0.0299 1.6743 0.4575 4.7000 4.7000 4.5822 0.2157 0.0948 0.1004 24.0740 0.0459 0.0169 0.1073 0.0179 0.0238 1.7368 0.4465 4.7000 4.7000 4.5807 0.2115 0.0845 0.0994 23.3009 0.0444 0.0160 0.0971 0.0174 0.0178 1.7994 0.4352 4.7000 4.7000 4.5793 0.2070 0.0746 0.0984 22.5734 0.0428 0.0151 0.0871 0.0169 0.0119 1.8619 0.4234 4.7000 4.7000 4.5778 0.2021 0.0649 0.0974 21.8878 0.0412 0.0141 0.0773 0.0164 0.0060 1.9245 0.4112 4.7000 4.7000 4.5766 0.1970 0.0555 0.0963 21.2408 0.0396 0.0132 0.0679 0.0158 0.0003 1.9870 0.3987 4.7000 4.7000 4.5756 0.1915 0.0464 0.0953 20.6292 0.0380 0.0123 0.0586 0.0152 -0.0053 2.0496 0.3857 4.7000 4.7000 4.5750 0.1858 0.0376 0.0943 20.0505 0.0364 0.0115 0.0497 0.0145 -0.0107 2.1121 0.3723 4.7000 4.7000 4.5743 0.1797 0.0291 0.0933 19.5022 0.0347 0.0106 0.0410 0.0138 -0.0160 2.1747 0.3586 4.7000 4.7000 4.5739 0.1734 0.0209 0.0922 18.9819 0.0331 0.0098 0.0325 0.0130 -0.0211 2.2372 0.3444 4.7000 4.7000 4.5727 0.1667 0.0130 0.0912 18.4877 0.0314 0.0089 0.0243 0.0122 -0.0261 2.2998 0.3299 4.7000 4.7000 4.5719 0.1598 0.0054 0.0902 18.0178 0.0297 0.0081 0.0164 0.0114 -0.0309 2.3623 0.3149 4.7000 4.7000 4.5711 0.1526 -0.0019 0.0892 17.5705 0.0281 0.0074 0.0087 0.0105 -0.0356 2.4249 0.2995 4.7000 4.7000 4.5709 0.1451 -0.0089 0.0881 17.1441 0.0264 0.0066 0.0013 0.0096 -0.0400 2.4874 0.2838 4.7000 4.7000 4.5713 0.1374 -0.0156 0.0871 16.7374 0.0247 0.0059 -0.0059 0.0086 -0.0443 2.5500 0.2676 4.7000 4.7000 4.5720 0.1294 -0.0221 0.0861 16.3490 0.0230 0.0052 -0.0128 0.0076 -0.0484 2.6100 0.2498 4.7000 4.7000 4.5737 0.1196 -0.0285 0.0851 15.9926 0.0213 0.0045 -0.0198 0.0056 -0.0524 2.6264 0.2417 4.7000 4.7000 4.5742 0.1139 -0.0311 0.0848 15.8976 0.0205 0.0042 -0.0226 0.0035 -0.0541 2.6403 0.2332 4.7000 4.7000 4.5746 0.1075 -0.0337 0.0846 15.8182 0.0197 0.0039 -0.0255 0.0009 -0.0557 2.6542 0.2230 4.7000 4.7000 4.5800 0.0994 -0.0367 0.0844 15.7395 0.0188 0.0036 -0.0289 -0.0027 -0.0577 2.6681 0.2107 4.7000 4.7000 4.5884 0.0893 -0.0403 0.0841 15.6616 0.0177 0.0032 -0.0329 -0.0073 -0.0600 2.6819 0.1959 4.7000 4.7000 4.6008 0.0767 -0.0445 0.0839 15.5845 0.0164 0.0027 -0.0376 -0.0133 -0.0628 2.6958 0.1775 4.7000 4.7000 4.6197 0.0607 -0.0496 0.0837 15.5080 0.0149 0.0022 -0.0433 -0.0210 -0.0661 2.7097 0.1534 4.7000 4.7000 4.6521 0.0393 -0.0562 0.0835 15.4323 0.0128 0.0017 -0.0507 -0.0317 -0.0704 2.7236 0.1161 4.7000 4.7000 4.7316 0.0051 -0.0662 0.0832 15.3574 0.0097 0.0010 -0.0620 -0.0491 -0.0770 2.7375 0.0606 4.7000 4.7000 5.0351 -0.0467 -0.0808 0.0830 15.2831 0.0050 0.0003 -0.0787 -0.0759 -0.0868 2.7500 0.0107 4.7000 4.7024 4.7024 -0.0933 -0.0939 0.0828 15.2242 0.0009 0.0000 -0.0939 0.0000 0.0000 RADIUS: 2.75 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.73 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.009424 TOTAL WEIGHT (Kg) = 0.004274 TOTAL VOLUME (IN**3) = 0.153525 TOTAL PROJECTED AREA (IN**2) = 2.1126 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000026 MOMENT OF INERTIA (Kg-M**2) = 0.000003 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003661 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 97.297 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28167.82 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.80, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.30, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412