4.5x4.1E (45x41E.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 4.1000 0.0000 0.0000 0.2500 0.0000 0.3029 0.0000 0.1514 0.0000 0.0750 0.0000 0.0000 0.0600 0.4796 4.1000 0.0093 -0.1869 0.2469 0.0088 0.2773 1.4091 0.1330 0.0827 0.0817 0.0061 -0.0191 0.1200 0.4572 4.1000 0.0721 -0.3610 0.2437 0.0324 0.2538 5.4645 0.1161 0.0839 0.0994 0.0151 -0.0097 0.1800 0.4381 4.1000 0.2365 -0.4552 0.2406 0.0667 0.2326 11.8129 0.1019 0.0816 0.1231 0.0259 0.0043 0.2400 0.4275 4.1000 0.5430 -0.3947 0.2377 0.1078 0.2136 19.8040 0.0913 0.0759 0.1507 0.0375 0.0219 0.3000 0.4288 4.1000 1.0179 -0.1205 0.2352 0.1521 0.1967 28.3698 0.0843 0.0682 0.1813 0.0490 0.0420 0.3600 0.4412 4.1000 1.6600 0.3999 0.2333 0.1956 0.1820 36.2750 0.0803 0.0597 0.2132 0.0596 0.0634 0.4200 0.4605 4.1000 2.4226 1.1489 0.2319 0.2347 0.1695 42.5528 0.0781 0.0515 0.2440 0.0684 0.0849 0.4800 0.4806 4.1000 3.1977 2.0330 0.2314 0.2656 0.1593 46.6760 0.0765 0.0440 0.2699 0.0747 0.1050 0.5400 0.4954 4.1000 3.8191 2.8685 0.2318 0.2846 0.1511 48.3817 0.0749 0.0377 0.2869 0.0777 0.1218 0.6000 0.5004 4.1000 4.0975 3.3908 0.2333 0.2878 0.1452 47.3841 0.0727 0.0327 0.2898 0.0762 0.1327 0.6595 0.4977 4.1000 4.1000 3.6004 0.2352 0.2796 0.1415 44.6946 0.0704 0.0287 0.2819 0.0721 0.1378 0.7109 0.4936 4.1000 4.1000 3.7272 0.2366 0.2714 0.1400 42.5469 0.0691 0.0258 0.2739 0.0695 0.1403 0.7619 0.4892 4.1000 4.1000 3.8200 0.2376 0.2623 0.1394 40.5788 0.0682 0.0235 0.2651 0.0675 0.1408 0.8128 0.4844 4.1000 4.1000 3.8878 0.2382 0.2523 0.1388 38.7568 0.0672 0.0217 0.2554 0.0660 0.1392 0.8638 0.4794 4.1000 4.1000 3.9323 0.2386 0.2412 0.1382 37.0685 0.0663 0.0203 0.2447 0.0649 0.1356 0.9147 0.4740 4.1000 4.1000 3.9546 0.2386 0.2292 0.1376 35.5023 0.0652 0.0193 0.2332 0.0640 0.1302 0.9657 0.4684 4.1000 4.1000 3.9564 0.2383 0.2171 0.1370 34.0477 0.0642 0.0187 0.2215 0.0634 0.1238 1.0166 0.4624 4.1000 4.1000 3.9531 0.2377 0.2052 0.1364 32.6946 0.0631 0.0182 0.2100 0.0629 0.1171 1.0676 0.4561 4.1000 4.1000 3.9502 0.2368 0.1935 0.1358 31.4343 0.0619 0.0176 0.1987 0.0624 0.1104 1.1185 0.4495 4.1000 4.1000 3.9475 0.2355 0.1820 0.1351 30.2586 0.0608 0.0170 0.1877 0.0620 0.1036 1.1695 0.4427 4.1000 4.1000 3.9451 0.2340 0.1707 0.1345 29.1602 0.0596 0.0165 0.1768 0.0617 0.0968 1.2204 0.4355 4.1000 4.1000 3.9429 0.2322 0.1597 0.1339 28.1323 0.0583 0.0159 0.1662 0.0613 0.0899 1.2714 0.4280 4.1000 4.1000 3.9410 0.2301 0.1488 0.1333 27.1692 0.0570 0.0153 0.1557 0.0610 0.0831 1.3223 0.4202 4.1000 4.1000 3.9394 0.2277 0.1382 0.1327 26.2652 0.0558 0.0147 0.1455 0.0606 0.0762 1.3733 0.4120 4.1000 4.1000 3.9381 0.2251 0.1278 0.1321 25.4155 0.0544 0.0140 0.1355 0.0602 0.0694 1.4242 0.4036 4.1000 4.1000 3.9372 0.2221 0.1176 0.1315 24.6158 0.0531 0.0134 0.1257 0.0597 0.0626 1.4752 0.3949 4.1000 4.1000 3.9366 0.2189 0.1077 0.1309 23.8620 0.0517 0.0128 0.1161 0.0592 0.0559 1.5261 0.3859 4.1000 4.1000 3.9362 0.2154 0.0980 0.1302 23.1505 0.0503 0.0122 0.1067 0.0586 0.0492 1.5771 0.3765 4.1000 4.1000 3.9354 0.2116 0.0884 0.1296 22.4780 0.0488 0.0116 0.0975 0.0576 0.0424 1.6280 0.3669 4.1000 4.1000 3.9345 0.2076 0.0791 0.1290 21.8417 0.0473 0.0111 0.0885 0.0563 0.0355 1.6790 0.3569 4.1000 4.1000 3.9335 0.2033 0.0700 0.1284 21.2388 0.0458 0.0107 0.0797 0.0548 0.0285 1.7299 0.3467 4.1000 4.1000 3.9327 0.1988 0.0611 0.1278 20.6668 0.0443 0.0102 0.0711 0.0530 0.0216 1.7809 0.3361 4.1000 4.1000 3.9323 0.1940 0.0525 0.1272 20.1236 0.0427 0.0098 0.0627 0.0512 0.0148 1.8318 0.3253 4.1000 4.1000 3.9326 0.1890 0.0441 0.1266 19.6071 0.0412 0.0093 0.0546 0.0493 0.0081 1.8828 0.3141 4.1000 4.1000 3.9337 0.1837 0.0360 0.1260 19.1155 0.0396 0.0088 0.0466 0.0475 0.0017 1.9337 0.3026 4.1000 4.1000 3.9355 0.1782 0.0282 0.1253 18.6471 0.0379 0.0083 0.0389 0.0457 -0.0044 1.9847 0.2908 4.1000 4.1000 3.9378 0.1724 0.0206 0.1247 18.2004 0.0363 0.0078 0.0313 0.0440 -0.0103 2.0356 0.2787 4.1000 4.1000 3.9408 0.1664 0.0134 0.1241 17.7738 0.0346 0.0072 0.0240 0.0425 -0.0158 2.0866 0.2661 4.1000 4.1000 3.9414 0.1600 0.0063 0.1235 17.3662 0.0329 0.0067 0.0168 0.0409 -0.0210 2.1354 0.2431 4.1000 4.1000 3.9396 0.1435 -0.0032 0.1229 16.9918 0.0299 0.0056 0.0066 0.0342 -0.0277 2.1489 0.2334 4.1000 4.1000 3.9437 0.1358 -0.0067 0.1227 16.8917 0.0287 0.0052 0.0027 0.0306 -0.0301 2.1602 0.2239 4.1000 4.1000 3.9504 0.1279 -0.0100 0.1226 16.8079 0.0274 0.0047 -0.0009 0.0269 -0.0324 2.1716 0.2128 4.1000 4.1000 3.9595 0.1185 -0.0138 0.1225 16.7248 0.0261 0.0043 -0.0051 0.0224 -0.0350 2.1830 0.1997 4.1000 4.1000 3.9721 0.1074 -0.0180 0.1223 16.6426 0.0244 0.0038 -0.0099 0.0169 -0.0379 2.1943 0.1842 4.1000 4.1000 3.9903 0.0937 -0.0230 0.1222 16.5612 0.0225 0.0032 -0.0154 0.0101 -0.0412 2.2057 0.1649 4.1000 4.1000 4.0185 0.0766 -0.0289 0.1221 16.4805 0.0201 0.0026 -0.0221 0.0014 -0.0452 2.2170 0.1390 4.1000 4.1000 4.0696 0.0529 -0.0366 0.1219 16.4006 0.0169 0.0018 -0.0309 -0.0108 -0.0504 2.2284 0.0977 4.1000 4.1000 4.2092 0.0146 -0.0486 0.1218 16.3214 0.0119 0.0009 -0.0446 -0.0308 -0.0585 2.2398 0.0522 4.1000 4.1000 4.6176 -0.0278 -0.0617 0.1217 16.2430 0.0063 0.0003 -0.0595 -0.0530 -0.0672 2.2500 0.0112 4.1000 4.1021 4.1021 -0.0660 -0.0733 0.1215 16.1807 0.0014 0.0000 -0.0733 0.0000 0.0000 RADIUS: 2.25 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.60 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.007575 TOTAL WEIGHT (Kg) = 0.003435 TOTAL VOLUME (IN**3) = 0.123402 TOTAL PROJECTED AREA (IN**2) = 1.5690 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000013 MOMENT OF INERTIA (Kg-M**2) = 0.000002 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002330 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 = 112.492 INNER LIMIT (NORMALIZED BY RADIUS) = 0.111 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 43269.34 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.50, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.20, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412