4x4E-3 (4x4E-3.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) 0.1245 0.4313 0.6171 0.0000 -0.3198 0.2156 0.0000 0.2020 0.0000 0.0871 0.0000 0.0900 0.0000 0.0000 0.1600 0.4000 0.7878 0.0209 -0.4299 0.2000 0.0046 0.1932 1.1920 0.0773 0.0591 0.0922 0.0074 -0.0006 0.1956 0.3863 0.9536 0.0988 -0.5042 0.1925 0.0172 0.1847 4.5940 0.0714 0.0594 0.0983 0.0070 0.0003 0.2312 0.3889 1.1147 0.2438 -0.5170 0.1916 0.0357 0.1768 9.5275 0.0687 0.0619 0.1070 0.0067 0.0019 0.2667 0.4011 1.2709 0.4555 -0.3656 0.1920 0.0579 0.1693 15.2074 0.0679 0.0610 0.1169 0.0056 0.0068 0.3022 0.4213 1.4223 0.7237 -0.0432 0.1928 0.0820 0.1622 20.8618 0.0683 0.0566 0.1271 0.0039 0.0142 0.3378 0.4473 1.5690 1.0298 0.4099 0.1941 0.1060 0.1555 25.8815 0.0696 0.0498 0.1375 0.0021 0.0231 0.3733 0.4760 1.7107 1.3496 0.9320 0.1960 0.1280 0.1493 29.9121 0.0711 0.0419 0.1478 0.0003 0.0319 0.4089 0.5038 1.8477 1.6558 1.4160 0.1985 0.1462 0.1434 32.8012 0.0723 0.0343 0.1572 -0.0009 0.0397 0.4444 0.5268 1.9799 1.9188 1.8102 0.2017 0.1585 0.1380 34.4936 0.0727 0.0278 0.1646 0.0002 0.0468 0.4800 0.5416 2.1072 2.1065 2.0604 0.2055 0.1632 0.1329 34.9333 0.0720 0.0248 0.1676 0.0017 0.0499 0.5162 0.5505 2.2319 2.2319 2.1932 0.2099 0.1624 0.1282 34.5343 0.0706 0.0247 0.1669 0.0020 0.0487 0.5633 0.5603 2.3867 2.3867 2.3572 0.2149 0.1610 0.1226 33.9942 0.0687 0.0246 0.1656 0.0021 0.0471 0.6110 0.5686 2.5350 2.5350 2.5144 0.2191 0.1592 0.1176 33.4368 0.0669 0.0244 0.1639 0.0019 0.0455 0.6588 0.5752 2.6746 2.6746 2.6621 0.2225 0.1570 0.1133 32.8696 0.0652 0.0242 0.1619 0.0014 0.0439 0.7065 0.5801 2.8056 2.8056 2.7999 0.2252 0.1544 0.1096 32.2932 0.0636 0.0240 0.1596 0.0007 0.0422 0.7542 0.5835 2.9278 2.9278 2.9278 0.2271 0.1514 0.1064 31.7077 0.0621 0.0238 0.1569 -0.0003 0.0404 0.8020 0.5854 3.0414 3.0414 3.0451 0.2283 0.1481 0.1039 31.1134 0.0608 0.0236 0.1540 -0.0015 0.0386 0.8497 0.5858 3.1462 3.1462 3.1518 0.2288 0.1445 0.1019 30.5105 0.0597 0.0235 0.1508 -0.0028 0.0368 0.8975 0.5848 3.2429 3.2429 3.2482 0.2287 0.1406 0.1005 29.9025 0.0588 0.0233 0.1474 -0.0043 0.0349 0.9452 0.5826 3.3347 3.3347 3.3378 0.2279 0.1364 0.0996 29.3140 0.0580 0.0232 0.1437 -0.0059 0.0329 0.9929 0.5790 3.4223 3.4223 3.4226 0.2265 0.1320 0.0988 28.7468 0.0572 0.0229 0.1398 -0.0075 0.0308 1.0407 0.5743 3.5058 3.5058 3.5027 0.2245 0.1274 0.0979 28.1979 0.0562 0.0227 0.1358 -0.0093 0.0286 1.0884 0.5684 3.5851 3.5851 3.5783 0.2220 0.1227 0.0971 27.6648 0.0552 0.0223 0.1315 -0.0111 0.0263 1.1362 0.5614 3.6602 3.6602 3.6494 0.2189 0.1178 0.0962 27.1455 0.0540 0.0219 0.1271 -0.0131 0.0240 1.1839 0.5534 3.7312 3.7312 3.7161 0.2153 0.1128 0.0954 26.6381 0.0528 0.0214 0.1226 -0.0150 0.0216 1.2316 0.5445 3.7980 3.7980 3.7784 0.2112 0.1077 0.0945 26.1412 0.0515 0.0208 0.1179 -0.0171 0.0192 1.2794 0.5347 3.8607 3.8607 3.8364 0.2067 0.1026 0.0937 25.6535 0.0501 0.0202 0.1131 -0.0191 0.0169 1.3271 0.5240 3.9192 3.9192 3.8903 0.2018 0.0974 0.0928 25.1738 0.0487 0.0195 0.1083 -0.0211 0.0146 1.3749 0.5126 3.9735 3.9735 3.9400 0.1964 0.0922 0.0920 24.7012 0.0472 0.0187 0.1034 -0.0231 0.0123 1.4226 0.5004 4.0237 4.0237 3.9859 0.1907 0.0870 0.0912 24.2350 0.0456 0.0179 0.0984 -0.0251 0.0101 1.4703 0.4877 4.0697 4.0697 4.0281 0.1846 0.0818 0.0903 23.7742 0.0440 0.0171 0.0934 -0.0271 0.0080 1.5181 0.4743 4.1115 4.1115 4.0665 0.1782 0.0767 0.0895 23.3184 0.0424 0.0162 0.0883 -0.0291 0.0059 1.5658 0.4604 4.1492 4.1492 4.1013 0.1715 0.0716 0.0886 22.8669 0.0408 0.0153 0.0833 -0.0310 0.0040 1.6136 0.4461 4.1827 4.1827 4.1328 0.1645 0.0666 0.0878 22.4192 0.0392 0.0144 0.0783 -0.0329 0.0021 1.6613 0.4313 4.2120 4.2120 4.1611 0.1573 0.0617 0.0869 21.9750 0.0375 0.0135 0.0734 -0.0347 0.0004 1.7090 0.4163 4.2372 4.2372 4.1862 0.1499 0.0569 0.0861 21.5338 0.0358 0.0126 0.0685 -0.0365 -0.0012 1.7568 0.4009 4.2582 4.2582 4.2084 0.1422 0.0523 0.0853 21.0953 0.0342 0.0117 0.0636 -0.0383 -0.0027 1.8045 0.3847 4.2751 4.2751 4.2232 0.1337 0.0475 0.0844 20.6592 0.0325 0.0107 0.0584 -0.0404 -0.0045 1.8523 0.3587 4.2878 4.2878 4.2272 0.1162 0.0396 0.0836 20.2252 0.0300 0.0093 0.0495 -0.0471 -0.0087 1.8980 0.3194 4.2961 4.2961 4.2287 0.0857 0.0274 0.0828 19.8108 0.0264 0.0074 0.0359 -0.0607 -0.0159 1.9101 0.3058 4.2976 4.2976 4.2312 0.0745 0.0232 0.0825 19.7018 0.0252 0.0067 0.0312 -0.0659 -0.0184 1.9202 0.2929 4.2987 4.2987 4.2343 0.0638 0.0192 0.0824 19.6107 0.0241 0.0062 0.0267 -0.0710 -0.0208 1.9303 0.2783 4.2996 4.2996 4.2386 0.0515 0.0147 0.0822 19.5196 0.0229 0.0056 0.0217 -0.0769 -0.0235 1.9404 0.2616 4.3003 4.3003 4.2453 0.0371 0.0095 0.0820 19.4286 0.0215 0.0049 0.0160 -0.0839 -0.0266 1.9505 0.2419 4.3008 4.3008 4.2562 0.0199 0.0034 0.0818 19.3377 0.0198 0.0042 0.0092 -0.0924 -0.0302 1.9606 0.2172 4.3012 4.3012 4.2762 -0.0020 -0.0043 0.0817 19.2468 0.0177 0.0034 0.0008 -0.1034 -0.0348 1.9707 0.1816 4.3013 4.3013 4.3227 -0.0343 -0.0156 0.0815 19.1560 0.0148 0.0024 -0.0113 -0.1198 -0.0414 1.9808 0.1301 4.3013 4.3013 4.4488 -0.0816 -0.0319 0.0813 19.0652 0.0106 0.0013 -0.0289 -0.1440 -0.0509 1.9909 0.0785 4.3011 4.3011 4.7550 -0.1292 -0.0481 0.0811 18.9745 0.0064 0.0005 -0.0463 -0.1682 -0.0601 2.0000 0.0321 4.3007 4.3029 4.3029 -0.1719 -0.0626 0.0810 18.9020 0.0026 0.0000 -0.0626 0.0000 0.0000 RADIUS: 2.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.48 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.008379 TOTAL WEIGHT (Kg) = 0.003800 TOTAL VOLUME (IN**3) = 0.136504 TOTAL PROJECTED AREA (IN**2) = 2.4396 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000019 MOMENT OF INERTIA (Kg-M**2) = 0.000002 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002197 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 = 170.677 INNER LIMIT (NORMALIZED BY RADIUS) = 0.125 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 40535.50 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.53, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.92, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412