6x4.2E-3 (6x42E-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) 0.1225 0.4244 1.7486 0.0000 -0.3892 0.2122 0.0000 0.2615 0.0000 0.1110 0.0000 0.1000 0.0000 0.0000 0.1702 0.4017 1.9835 0.1530 -0.4456 0.1988 0.0285 0.2510 8.1380 0.1008 0.0715 0.1034 0.0003 -0.0045 0.2180 0.4147 2.2026 0.3986 -0.3803 0.1997 0.0580 0.2409 16.2270 0.0999 0.0733 0.1116 0.0014 -0.0030 0.2657 0.4370 2.4063 0.7306 -0.1584 0.2026 0.0876 0.2312 23.6304 0.1010 0.0722 0.1230 0.0041 0.0009 0.3135 0.4664 2.5952 1.1340 0.2197 0.2070 0.1162 0.2217 29.9295 0.1034 0.0691 0.1376 0.0079 0.0069 0.3613 0.5001 2.7698 1.5867 0.7381 0.2127 0.1431 0.2127 34.9557 0.1064 0.0645 0.1552 0.0125 0.0147 0.4090 0.5350 2.9306 2.0597 1.3238 0.2192 0.1672 0.2040 38.7126 0.1091 0.0596 0.1743 0.0166 0.0228 0.4568 0.5684 3.0783 2.5192 1.9350 0.2262 0.1876 0.1956 41.2777 0.1112 0.0541 0.1924 0.0215 0.0327 0.5045 0.5978 3.2133 2.9284 2.5001 0.2334 0.2034 0.1877 42.7326 0.1122 0.0487 0.2072 0.0268 0.0437 0.5523 0.6212 3.3362 3.2496 2.9426 0.2405 0.2136 0.1801 43.1226 0.1119 0.0444 0.2173 0.0314 0.0540 0.6000 0.6372 3.4476 3.4467 3.2027 0.2470 0.2174 0.1728 42.4355 0.1101 0.0424 0.2212 0.0330 0.0599 0.6492 0.6485 3.5509 3.5509 3.3218 0.2534 0.2168 0.1658 41.0391 0.1075 0.0422 0.2209 0.0317 0.0618 0.7237 0.6627 3.6862 3.6862 3.4807 0.2620 0.2153 0.1559 39.0306 0.1033 0.0417 0.2200 0.0299 0.0648 0.7996 0.6739 3.8001 3.8001 3.6199 0.2695 0.2132 0.1467 37.1025 0.0989 0.0409 0.2185 0.0278 0.0676 0.8756 0.6819 3.8920 3.8920 3.7363 0.2759 0.2105 0.1385 35.2778 0.0945 0.0399 0.2165 0.0262 0.0705 0.9515 0.6870 3.9639 3.9639 3.8313 0.2811 0.2071 0.1314 33.5456 0.0902 0.0388 0.2139 0.0245 0.0730 1.0274 0.6891 4.0182 4.0182 3.9060 0.2851 0.2032 0.1252 31.8992 0.0863 0.0376 0.2109 0.0230 0.0752 1.1034 0.6886 4.0569 4.0569 3.9617 0.2881 0.1988 0.1200 30.3349 0.0827 0.0365 0.2074 0.0216 0.0770 1.1793 0.6855 4.0822 4.0822 4.0001 0.2901 0.1938 0.1159 28.8509 0.0795 0.0355 0.2034 0.0203 0.0784 1.2553 0.6800 4.0964 4.0964 4.0226 0.2911 0.1884 0.1128 27.4467 0.0767 0.0346 0.1991 0.0193 0.0794 1.3312 0.6723 4.1023 4.1023 4.0319 0.2911 0.1826 0.1108 26.1260 0.0745 0.0337 0.1944 0.0185 0.0799 1.4071 0.6624 4.1068 4.1068 4.0348 0.2902 0.1764 0.1098 24.9146 0.0727 0.0330 0.1893 0.0180 0.0798 1.4831 0.6506 4.1112 4.1112 4.0363 0.2884 0.1699 0.1091 23.8066 0.0710 0.0321 0.1840 0.0179 0.0792 1.5590 0.6370 4.1157 4.1157 4.0374 0.2857 0.1633 0.1084 22.7900 0.0691 0.0311 0.1783 0.0178 0.0781 1.6350 0.6217 4.1202 4.1202 4.0370 0.2823 0.1565 0.1077 21.8545 0.0670 0.0299 0.1724 0.0180 0.0767 1.7109 0.6049 4.1246 4.1246 4.0353 0.2781 0.1497 0.1070 20.9913 0.0647 0.0286 0.1663 0.0183 0.0749 1.7868 0.5867 4.1291 4.1291 4.0334 0.2732 0.1429 0.1063 20.1925 0.0624 0.0272 0.1600 0.0188 0.0729 1.8628 0.5674 4.1336 4.1336 4.0320 0.2675 0.1360 0.1056 19.4516 0.0599 0.0257 0.1535 0.0194 0.0707 1.9387 0.5469 4.1380 4.1380 4.0305 0.2613 0.1291 0.1049 18.7627 0.0574 0.0240 0.1468 0.0201 0.0683 2.0147 0.5256 4.1425 4.1425 4.0291 0.2544 0.1223 0.1042 18.1207 0.0547 0.0223 0.1400 0.0210 0.0658 2.0906 0.5035 4.1470 4.1470 4.0286 0.2470 0.1155 0.1035 17.5211 0.0521 0.0206 0.1331 0.0218 0.0631 2.1665 0.4807 4.1514 4.1514 4.0297 0.2391 0.1088 0.1028 16.9599 0.0494 0.0189 0.1262 0.0226 0.0604 2.2425 0.4576 4.1559 4.1559 4.0326 0.2306 0.1022 0.1020 16.4337 0.0467 0.0172 0.1192 0.0234 0.0576 2.3184 0.4341 4.1604 4.1604 4.0378 0.2217 0.0957 0.1013 15.9394 0.0440 0.0155 0.1122 0.0241 0.0547 2.3944 0.4104 4.1648 4.1648 4.0457 0.2124 0.0893 0.1006 15.4742 0.0413 0.0138 0.1052 0.0247 0.0518 2.4703 0.3867 4.1693 4.1693 4.0566 0.2028 0.0830 0.0999 15.0357 0.0386 0.0123 0.0983 0.0250 0.0488 2.5462 0.3632 4.1738 4.1738 4.0700 0.1928 0.0768 0.0992 14.6217 0.0360 0.0108 0.0914 0.0250 0.0458 2.6222 0.3399 4.1782 4.1782 4.0851 0.1825 0.0708 0.0985 14.2302 0.0335 0.0095 0.0846 0.0247 0.0426 2.6981 0.3171 4.1827 4.1827 4.1028 0.1720 0.0649 0.0978 13.8596 0.0310 0.0083 0.0780 0.0240 0.0394 2.7741 0.2949 4.1872 4.1872 4.1213 0.1612 0.0592 0.0971 13.5081 0.0286 0.0071 0.0714 0.0228 0.0360 2.8468 0.2718 4.1915 4.1915 4.1199 0.1483 0.0533 0.0964 13.1880 0.0262 0.0061 0.0642 0.0201 0.0318 2.8652 0.2624 4.1925 4.1925 4.1148 0.1415 0.0510 0.0963 13.1099 0.0253 0.0057 0.0614 0.0175 0.0301 2.8803 0.2530 4.1934 4.1934 4.1124 0.1341 0.0487 0.0961 13.0459 0.0243 0.0053 0.0586 0.0144 0.0285 2.8955 0.2417 4.1943 4.1943 4.1156 0.1249 0.0461 0.0960 12.9827 0.0232 0.0048 0.0553 0.0103 0.0265 2.9106 0.2282 4.1952 4.1952 4.1223 0.1135 0.0429 0.0958 12.9200 0.0219 0.0043 0.0514 0.0050 0.0242 2.9258 0.2119 4.1961 4.1961 4.1352 0.0994 0.0392 0.0957 12.8580 0.0203 0.0037 0.0469 -0.0017 0.0215 2.9409 0.1918 4.1970 4.1970 4.1600 0.0815 0.0346 0.0956 12.7965 0.0183 0.0031 0.0414 -0.0105 0.0183 2.9561 0.1656 4.1979 4.1979 4.2126 0.0575 0.0287 0.0954 12.7357 0.0158 0.0023 0.0344 -0.0224 0.0144 2.9712 0.1247 4.1988 4.1988 4.3659 0.0191 0.0197 0.0953 12.6755 0.0119 0.0013 0.0238 -0.0419 0.0085 2.9864 0.0652 4.1997 4.1997 4.9917 -0.0374 0.0066 0.0951 12.6158 0.0062 0.0004 0.0087 -0.0709 0.0003 3.0000 0.0117 4.2005 4.2025 4.2025 -0.0883 -0.0050 0.0950 12.5685 0.0011 0.0000 -0.0050 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.60 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.011540 TOTAL WEIGHT (Kg) = 0.005234 TOTAL VOLUME (IN**3) = 0.266345 TOTAL PROJECTED AREA (IN**2) = 4.0340 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000051 MOMENT OF INERTIA (Kg-M**2) = 0.000006 STATIC MOMENT, ONE SIDE (IN-LB) = 0.004205 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.200 DENSITY (INPUT FILE, LB/IN**3) = 0.4333E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.4333E-01 ACTIVITY FACTOR = 104.570 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19116.51 BASED ON MODULUS (MILLION) = 1.00 AND, MATERIAL DENSITY (S.G.) = 1.20 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.75, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.45, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412