7x4E (7x4E.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 4.0000 0.0000 0.0000 0.2500 0.0000 0.5500 0.0000 0.2750 0.0000 0.0500 0.0000 0.0000 0.0900 0.4738 4.0000 0.0117 -0.5168 0.2484 0.0037 0.5437 1.1841 0.2576 0.1087 0.0525 0.0089 -0.0777 0.1800 0.4512 4.0000 0.0916 -1.0059 0.2520 0.0140 0.5247 4.6326 0.2368 0.1053 0.0593 0.0245 -0.0749 0.2700 0.4364 4.0000 0.2999 -1.3512 0.2599 0.0294 0.4931 10.0247 0.2152 0.1013 0.0691 0.0427 -0.0699 0.3600 0.4334 4.0000 0.6779 -1.3604 0.2711 0.0485 0.4489 16.6825 0.1946 0.0931 0.0808 0.0622 -0.0617 0.4500 0.4447 4.0000 1.2328 -0.9291 0.2847 0.0697 0.3921 23.5581 0.1743 0.0829 0.0943 0.0814 -0.0508 0.5400 0.4697 4.0000 1.9249 -0.0606 0.2997 0.0919 0.3266 29.5671 0.1534 0.0722 0.1094 0.0986 -0.0374 0.6300 0.5057 4.0000 2.6652 1.1125 0.3152 0.1135 0.2705 33.9527 0.1368 0.0620 0.1255 0.1127 -0.0220 0.7200 0.5491 4.0000 3.3329 2.3347 0.3304 0.1331 0.2250 36.3806 0.1235 0.0532 0.1417 0.1224 -0.0050 0.8100 0.5967 4.0000 3.8069 3.2203 0.3442 0.1495 0.1890 36.7971 0.1128 0.0467 0.1564 0.1260 0.0122 0.9000 0.6470 4.0000 3.9984 3.6325 0.3558 0.1612 0.1613 35.2629 0.1044 0.0441 0.1679 0.1198 0.0259 0.9895 0.6951 4.0000 4.0000 3.7299 0.3650 0.1685 0.1410 32.7561 0.0980 0.0448 0.1761 0.1049 0.0345 1.0705 0.7315 4.0000 4.0000 3.7940 0.3719 0.1730 0.1278 30.7393 0.0935 0.0452 0.1816 0.0932 0.0420 1.1510 0.7612 4.0000 4.0000 3.8389 0.3775 0.1757 0.1188 28.9463 0.0905 0.0455 0.1853 0.0830 0.0486 1.2316 0.7848 4.0000 4.0000 3.8680 0.3819 0.1766 0.1132 27.3356 0.0888 0.0460 0.1875 0.0744 0.0542 1.3121 0.8026 4.0000 4.0000 3.8844 0.3851 0.1757 0.1100 25.8828 0.0883 0.0467 0.1881 0.0673 0.0586 1.3926 0.8149 4.0000 4.0000 3.8918 0.3873 0.1731 0.1086 24.5675 0.0885 0.0474 0.1872 0.0616 0.0616 1.4731 0.8221 4.0000 4.0000 3.8941 0.3883 0.1692 0.1080 23.3722 0.0888 0.0479 0.1850 0.0569 0.0634 1.5536 0.8245 4.0000 4.0000 3.8948 0.3882 0.1640 0.1076 22.2821 0.0887 0.0481 0.1815 0.0532 0.0639 1.6341 0.8224 4.0000 4.0000 3.8949 0.3872 0.1577 0.1072 21.2847 0.0882 0.0479 0.1768 0.0503 0.0632 1.7147 0.8161 4.0000 4.0000 3.8944 0.3852 0.1505 0.1069 20.3690 0.0872 0.0473 0.1710 0.0482 0.0614 1.7952 0.8061 4.0000 4.0000 3.8931 0.3822 0.1425 0.1065 19.5260 0.0859 0.0464 0.1642 0.0468 0.0587 1.8757 0.7925 4.0000 4.0000 3.8909 0.3784 0.1337 0.1062 18.7475 0.0841 0.0452 0.1565 0.0460 0.0550 1.9562 0.7757 4.0000 4.0000 3.8874 0.3737 0.1243 0.1058 18.0267 0.0821 0.0437 0.1480 0.0458 0.0505 2.0367 0.7561 4.0000 4.0000 3.8827 0.3682 0.1144 0.1055 17.3577 0.0798 0.0419 0.1386 0.0461 0.0453 2.1172 0.7340 4.0000 4.0000 3.8771 0.3619 0.1040 0.1052 16.7352 0.0772 0.0399 0.1287 0.0469 0.0394 2.1978 0.7097 4.0000 4.0000 3.8706 0.3549 0.0932 0.1049 16.1546 0.0744 0.0377 0.1181 0.0481 0.0330 2.2783 0.6835 4.0000 4.0000 3.8639 0.3472 0.0821 0.1046 15.6120 0.0715 0.0354 0.1070 0.0496 0.0262 2.3588 0.6558 4.0000 4.0000 3.8572 0.3388 0.0708 0.1043 15.1038 0.0684 0.0329 0.0956 0.0513 0.0189 2.4393 0.6269 4.0000 4.0000 3.8508 0.3298 0.0593 0.1040 14.6270 0.0652 0.0304 0.0838 0.0531 0.0113 2.5198 0.5971 4.0000 4.0000 3.8449 0.3202 0.0478 0.1037 14.1787 0.0619 0.0278 0.0718 0.0550 0.0035 2.6003 0.5667 4.0000 4.0000 3.8398 0.3101 0.0362 0.1035 13.7566 0.0586 0.0253 0.0596 0.0568 -0.0046 2.6809 0.5361 4.0000 4.0000 3.8356 0.2995 0.0247 0.1032 13.3585 0.0553 0.0229 0.0474 0.0585 -0.0128 2.7614 0.5056 4.0000 4.0000 3.8327 0.2884 0.0133 0.1030 12.9824 0.0521 0.0205 0.0352 0.0598 -0.0210 2.8419 0.4756 4.0000 4.0000 3.8279 0.2769 0.0021 0.1028 12.6265 0.0489 0.0183 0.0229 0.0607 -0.0294 2.9224 0.4462 4.0000 4.0000 3.8195 0.2650 -0.0089 0.1025 12.2893 0.0458 0.0162 0.0108 0.0611 -0.0380 3.0029 0.4180 4.0000 4.0000 3.8072 0.2528 -0.0196 0.1023 11.9695 0.0428 0.0143 -0.0013 0.0608 -0.0466 3.0834 0.3912 4.0000 4.0000 3.7899 0.2403 -0.0299 0.1021 11.6656 0.0399 0.0126 -0.0130 0.0597 -0.0552 3.1640 0.3660 4.0000 4.0000 3.7668 0.2275 -0.0397 0.1019 11.3765 0.0373 0.0111 -0.0244 0.0577 -0.0636 3.2445 0.3430 4.0000 4.0000 3.7358 0.2145 -0.0491 0.1017 11.1013 0.0349 0.0098 -0.0353 0.0547 -0.0718 3.3217 0.3178 4.0000 4.0000 3.6287 0.1966 -0.0585 0.1015 10.8494 0.0323 0.0085 -0.0463 0.0480 -0.0800 3.3427 0.3068 4.0000 4.0000 3.5899 0.1872 -0.0619 0.1015 10.7830 0.0311 0.0079 -0.0502 0.0436 -0.0827 3.3604 0.2956 4.0000 4.0000 3.5675 0.1773 -0.0650 0.1015 10.7276 0.0300 0.0073 -0.0539 0.0387 -0.0852 3.3780 0.2824 4.0000 4.0000 3.5501 0.1652 -0.0685 0.1014 10.6727 0.0286 0.0067 -0.0581 0.0325 -0.0879 3.3957 0.2666 4.0000 4.0000 3.5404 0.1504 -0.0724 0.1014 10.6184 0.0270 0.0060 -0.0627 0.0250 -0.0909 3.4134 0.2476 4.0000 4.0000 3.5436 0.1324 -0.0769 0.1014 10.5647 0.0251 0.0052 -0.0681 0.0155 -0.0943 3.4311 0.2240 4.0000 4.0000 3.5709 0.1096 -0.0823 0.1013 10.5115 0.0227 0.0043 -0.0743 0.0035 -0.0981 3.4487 0.1925 4.0000 4.0000 3.6524 0.0790 -0.0889 0.1013 10.4588 0.0195 0.0032 -0.0823 -0.0127 -0.1028 3.4664 0.1416 4.0000 4.0000 3.9284 0.0290 -0.0991 0.1012 10.4066 0.0143 0.0017 -0.0943 -0.0394 -0.1095 3.4841 0.0745 4.0000 4.0000 4.6097 -0.0370 -0.1121 0.1012 10.3550 0.0075 0.0005 -0.1096 -0.0746 -0.1179 3.5000 0.0144 4.0000 4.0020 4.0020 -0.0963 -0.1235 0.1012 10.3140 0.0015 0.0000 -0.1235 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.90 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.019112 TOTAL WEIGHT (Kg) = 0.008668 TOTAL VOLUME (IN**3) = 0.311358 TOTAL PROJECTED AREA (IN**2) = 3.8268 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000108 MOMENT OF INERTIA (Kg-M**2) = 0.000012 STATIC MOMENT, ONE SIDE (IN-LB) = 0.011300 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 = 108.383 INNER LIMIT (NORMALIZED BY RADIUS) = 0.071 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 22036.01 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.95, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.36, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412