5x3.7E-3 (5x37E-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 2.3956 0.0000 -0.3933 0.2122 0.0000 0.2690 0.0000 0.1141 0.0000 0.0950 0.0000 0.0000 0.1602 0.3950 2.4814 0.1199 -0.4517 0.1995 0.0243 0.2588 6.7886 0.1022 0.0657 0.0990 0.0093 -0.0071 0.1980 0.3891 2.5640 0.3238 -0.4367 0.1991 0.0524 0.2492 14.5900 0.0970 0.0656 0.1093 0.0161 -0.0040 0.2357 0.3970 2.6435 0.6125 -0.2772 0.2009 0.0827 0.2400 22.4637 0.0953 0.0636 0.1232 0.0226 0.0035 0.2735 0.4160 2.7198 0.9751 0.0459 0.2038 0.1138 0.2314 29.5708 0.0963 0.0601 0.1403 0.0284 0.0145 0.3113 0.4430 2.7930 1.3892 0.5186 0.2078 0.1443 0.2232 35.3891 0.0989 0.0557 0.1602 0.0335 0.0276 0.3490 0.4739 2.8630 1.8234 1.0761 0.2125 0.1726 0.2155 39.7449 0.1021 0.0512 0.1818 0.0374 0.0410 0.3867 0.5047 2.9299 2.2433 1.6440 0.2177 0.1974 0.2083 42.7117 0.1051 0.0464 0.2029 0.0408 0.0546 0.4245 0.5316 2.9936 2.6147 2.1687 0.2233 0.2171 0.2014 44.4300 0.1071 0.0418 0.2208 0.0444 0.0682 0.4622 0.5519 3.0541 2.9025 2.5787 0.2289 0.2304 0.1950 44.9815 0.1076 0.0381 0.2334 0.0476 0.0802 0.5000 0.5633 3.1115 3.0734 2.8125 0.2344 0.2358 0.1891 44.3717 0.1065 0.0362 0.2388 0.0491 0.0880 0.5391 0.5695 3.1676 3.1546 2.9062 0.2400 0.2357 0.1833 42.9636 0.1044 0.0360 0.2391 0.0489 0.0918 0.6011 0.5816 3.2497 3.2497 3.0156 0.2480 0.2348 0.1750 40.7096 0.1018 0.0360 0.2388 0.0473 0.0961 0.6645 0.5939 3.3248 3.3248 3.1022 0.2553 0.2330 0.1676 38.5327 0.0995 0.0360 0.2378 0.0452 0.0993 0.7278 0.6037 3.3909 3.3909 3.1790 0.2615 0.2305 0.1611 36.5576 0.0973 0.0359 0.2361 0.0433 0.1019 0.7912 0.6113 3.4482 3.4482 3.2454 0.2667 0.2272 0.1556 34.7477 0.0951 0.0357 0.2336 0.0416 0.1039 0.8545 0.6166 3.4966 3.4966 3.3011 0.2710 0.2233 0.1510 33.0743 0.0931 0.0354 0.2306 0.0401 0.1052 0.9179 0.6198 3.5362 3.5362 3.3459 0.2743 0.2186 0.1471 31.5148 0.0912 0.0351 0.2269 0.0387 0.1058 0.9812 0.6209 3.5668 3.5668 3.3797 0.2767 0.2133 0.1440 30.0510 0.0894 0.0348 0.2227 0.0372 0.1059 1.0446 0.6200 3.5886 3.5886 3.4024 0.2781 0.2074 0.1417 28.6682 0.0878 0.0344 0.2179 0.0358 0.1054 1.1079 0.6172 3.6016 3.6016 3.4143 0.2786 0.2010 0.1399 27.3558 0.0864 0.0340 0.2127 0.0342 0.1042 1.1713 0.6126 3.6118 3.6118 3.4208 0.2783 0.1941 0.1388 26.1404 0.0850 0.0336 0.2070 0.0329 0.1025 1.2346 0.6062 3.6218 3.6218 3.4266 0.2770 0.1868 0.1378 25.0271 0.0835 0.0330 0.2009 0.0315 0.1003 1.2980 0.5982 3.6318 3.6318 3.4325 0.2749 0.1793 0.1370 24.0041 0.0819 0.0323 0.1944 0.0302 0.0975 1.3613 0.5886 3.6416 3.6416 3.4382 0.2720 0.1716 0.1363 23.0614 0.0802 0.0314 0.1876 0.0288 0.0943 1.4247 0.5775 3.6513 3.6513 3.4438 0.2682 0.1636 0.1356 22.1903 0.0783 0.0304 0.1804 0.0275 0.0908 1.4881 0.5650 3.6609 3.6609 3.4497 0.2635 0.1556 0.1351 21.3832 0.0763 0.0293 0.1731 0.0260 0.0869 1.5514 0.5512 3.6704 3.6704 3.4556 0.2581 0.1474 0.1347 20.6334 0.0742 0.0282 0.1655 0.0245 0.0828 1.6148 0.5361 3.6798 3.6798 3.4614 0.2519 0.1392 0.1343 19.9354 0.0720 0.0269 0.1577 0.0228 0.0784 1.6781 0.5198 3.6891 3.6891 3.4672 0.2449 0.1310 0.1341 19.2840 0.0697 0.0255 0.1498 0.0211 0.0740 1.7415 0.5025 3.6983 3.6983 3.4727 0.2372 0.1228 0.1339 18.6748 0.0673 0.0240 0.1417 0.0193 0.0694 1.8048 0.4842 3.7073 3.7073 3.4776 0.2287 0.1147 0.1339 18.1039 0.0648 0.0225 0.1336 0.0173 0.0647 1.8682 0.4650 3.7163 3.7163 3.4822 0.2194 0.1067 0.1340 17.5679 0.0623 0.0210 0.1254 0.0152 0.0601 1.9315 0.4449 3.7251 3.7251 3.4863 0.2095 0.0987 0.1341 17.0636 0.0597 0.0194 0.1173 0.0129 0.0554 1.9949 0.4241 3.7339 3.7339 3.4893 0.1988 0.0910 0.1344 16.5885 0.0570 0.0178 0.1092 0.0103 0.0508 2.0582 0.4026 3.7425 3.7425 3.4910 0.1875 0.0833 0.1347 16.1400 0.0542 0.0162 0.1011 0.0076 0.0463 2.1216 0.3805 3.7510 3.7510 3.4916 0.1755 0.0760 0.1352 15.7159 0.0514 0.0146 0.0932 0.0046 0.0419 2.1849 0.3580 3.7594 3.7594 3.4913 0.1628 0.0688 0.1357 15.3144 0.0486 0.0130 0.0854 0.0012 0.0376 2.2483 0.3350 3.7677 3.7677 3.4915 0.1495 0.0619 0.1364 14.9338 0.0457 0.0115 0.0779 -0.0024 0.0335 2.3116 0.3075 3.7758 3.7758 3.4547 0.1316 0.0543 0.1372 14.5723 0.0422 0.0098 0.0690 -0.0086 0.0285 2.3724 0.2644 3.7836 3.7836 3.3662 0.0977 0.0433 0.1380 14.2426 0.0365 0.0073 0.0554 -0.0235 0.0208 2.3876 0.2500 3.7855 3.7855 3.3452 0.0857 0.0398 0.1382 14.1621 0.0345 0.0066 0.0511 -0.0292 0.0183 2.4003 0.2367 3.7871 3.7871 3.3297 0.0744 0.0365 0.1384 14.0962 0.0328 0.0059 0.0471 -0.0346 0.0160 2.4129 0.2219 3.7887 3.7887 3.3180 0.0616 0.0330 0.1386 14.0310 0.0308 0.0052 0.0427 -0.0408 0.0135 2.4255 0.2053 3.7903 3.7903 3.3136 0.0470 0.0290 0.1388 13.9665 0.0285 0.0045 0.0378 -0.0480 0.0108 2.4381 0.1863 3.7918 3.7918 3.3230 0.0301 0.0245 0.1390 13.9025 0.0259 0.0037 0.0323 -0.0565 0.0078 2.4508 0.1641 3.7934 3.7934 3.3593 0.0101 0.0193 0.1392 13.8392 0.0228 0.0029 0.0260 -0.0666 0.0043 2.4634 0.1370 3.7950 3.7950 3.4560 -0.0147 0.0130 0.1394 13.7764 0.0191 0.0020 0.0185 -0.0793 0.0002 2.4760 0.1008 3.7965 3.7965 3.7212 -0.0485 0.0045 0.1396 13.7142 0.0141 0.0011 0.0085 -0.0967 -0.0052 2.4886 0.0541 3.7981 3.7981 4.5064 -0.0924 -0.0063 0.1398 13.6527 0.0076 0.0003 -0.0042 -0.1195 -0.0119 2.5000 0.0121 3.7995 3.8013 3.8013 -0.1320 -0.0159 0.1400 13.6038 0.0017 0.0000 -0.0159 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.50 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.009290 TOTAL WEIGHT (Kg) = 0.004213 TOTAL VOLUME (IN**3) = 0.214414 TOTAL PROJECTED AREA (IN**2) = 3.1179 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000033 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003097 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 = 126.490 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 24855.47 BASED ON MODULUS (MILLION) = 1.00 AND, MATERIAL DENSITY (S.G.) = 1.20 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.66, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.40, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412