22x12E (22x12E.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 1.3750 12.0000 0.0000 0.0000 0.6875 0.0000 0.3309 0.0000 0.4550 0.0000 0.2250 0.0000 0.0000 0.2860 1.2979 12.0000 0.0389 -0.6056 0.6768 0.0210 0.3257 1.2415 0.4227 0.5085 0.2396 0.0280 0.0051 0.5720 1.2414 12.0000 0.3020 -1.0203 0.6727 0.0772 0.3101 4.8025 0.3850 0.4861 0.2764 0.0560 0.0283 0.8580 1.2129 12.0000 0.9704 -0.9155 0.6742 0.1594 0.2854 10.2045 0.3461 0.4552 0.3297 0.0825 0.0647 1.1440 1.2186 12.0000 2.1451 -0.0704 0.6805 0.2584 0.2608 16.6163 0.3179 0.4202 0.3951 0.1066 0.1108 1.4300 1.2595 12.0000 3.8150 1.5740 0.6906 0.3653 0.2385 23.0059 0.3004 0.3845 0.4677 0.1274 0.1634 1.7160 1.3295 12.0000 5.8462 3.8872 0.7036 0.4710 0.2182 28.4674 0.2901 0.3501 0.5424 0.1441 0.2190 2.0020 1.4175 12.0000 7.9963 6.4227 0.7185 0.5664 0.1999 32.4437 0.2834 0.3187 0.6129 0.1561 0.2738 2.2880 1.5106 12.0000 9.9535 8.7244 0.7345 0.6426 0.1835 34.6976 0.2773 0.2924 0.6720 0.1624 0.3229 2.5740 1.5974 12.0000 11.3869 10.4446 0.7506 0.6903 0.1690 35.1484 0.2700 0.2734 0.7110 0.1611 0.3600 2.8600 1.6700 12.0000 11.9946 11.2511 0.7658 0.7007 0.1562 33.7224 0.2609 0.2654 0.7198 0.1480 0.3768 3.1442 1.7266 12.0000 12.0000 11.3639 0.7781 0.6848 0.1452 31.2753 0.2507 0.2661 0.7074 0.1245 0.3763 3.3979 1.7659 12.0000 12.0000 11.4474 0.7851 0.6699 0.1367 29.3393 0.2414 0.2657 0.6962 0.1042 0.3752 3.6497 1.7951 12.0000 12.0000 11.5187 0.7886 0.6549 0.1294 27.6226 0.2323 0.2649 0.6851 0.0839 0.3730 3.9016 1.8150 12.0000 12.0000 11.5772 0.7888 0.6396 0.1233 26.0821 0.2237 0.2639 0.6739 0.0638 0.3698 4.1534 1.8260 12.0000 12.0000 11.6217 0.7857 0.6242 0.1182 24.6942 0.2158 0.2628 0.6627 0.0440 0.3660 4.4053 1.8286 12.0000 12.0000 11.6502 0.7796 0.6089 0.1141 23.4385 0.2086 0.2616 0.6516 0.0249 0.3619 4.6572 1.8233 12.0000 12.0000 11.6594 0.7706 0.5937 0.1110 22.2980 0.2023 0.2601 0.6404 0.0068 0.3578 4.9090 1.8107 12.0000 12.0000 11.6417 0.7589 0.5788 0.1087 21.2585 0.1969 0.2581 0.6293 -0.0098 0.3540 5.1609 1.7912 12.0000 12.0000 11.6044 0.7446 0.5643 0.1073 20.3077 0.1923 0.2551 0.6182 -0.0247 0.3508 5.4128 1.7653 12.0000 12.0000 11.5624 0.7279 0.5504 0.1066 19.4351 0.1881 0.2508 0.6072 -0.0379 0.3485 5.6646 1.7335 12.0000 12.0000 11.5211 0.7090 0.5372 0.1059 18.6318 0.1836 0.2439 0.5961 -0.0492 0.3470 5.9165 1.6963 12.0000 12.0000 11.4831 0.6879 0.5248 0.1052 17.8902 0.1785 0.2347 0.5850 -0.0588 0.3466 6.1683 1.6542 12.0000 12.0000 11.4528 0.6649 0.5132 0.1046 17.2037 0.1731 0.2233 0.5739 -0.0667 0.3471 6.4202 1.6077 12.0000 12.0000 11.4309 0.6400 0.5022 0.1041 16.5665 0.1673 0.2103 0.5627 -0.0731 0.3483 6.6721 1.5573 12.0000 12.0000 11.4118 0.6135 0.4916 0.1035 15.9736 0.1612 0.1966 0.5516 -0.0790 0.3495 6.9239 1.5034 12.0000 12.0000 11.3935 0.5856 0.4813 0.1030 15.4207 0.1549 0.1827 0.5405 -0.0846 0.3503 7.1758 1.4466 12.0000 12.0000 11.3760 0.5563 0.4712 0.1026 14.9039 0.1484 0.1687 0.5293 -0.0900 0.3508 7.4277 1.3874 12.0000 12.0000 11.3593 0.5258 0.4614 0.1021 14.4200 0.1417 0.1548 0.5182 -0.0954 0.3509 7.6795 1.3262 12.0000 12.0000 11.3435 0.4943 0.4517 0.1018 13.9659 0.1349 0.1411 0.5071 -0.1007 0.3507 7.9314 1.2636 12.0000 12.0000 11.3286 0.4619 0.4422 0.1014 13.5389 0.1281 0.1279 0.4960 -0.1061 0.3500 8.1832 1.2000 12.0000 12.0000 11.3148 0.4288 0.4329 0.1011 13.1369 0.1213 0.1152 0.4848 -0.1116 0.3490 8.4351 1.1359 12.0000 12.0000 11.3019 0.3951 0.4238 0.1008 12.7577 0.1145 0.1031 0.4737 -0.1174 0.3475 8.6870 1.0719 12.0000 12.0000 11.2896 0.3610 0.4147 0.1006 12.3994 0.1078 0.0917 0.4626 -0.1234 0.3456 8.9388 1.0083 12.0000 12.0000 11.2785 0.3267 0.4057 0.1004 12.0604 0.1012 0.0812 0.4515 -0.1299 0.3433 9.1907 0.9458 12.0000 12.0000 11.2683 0.2923 0.3968 0.1002 11.7392 0.0948 0.0714 0.4403 -0.1368 0.3405 9.4426 0.8849 12.0000 12.0000 11.2589 0.2579 0.3879 0.1000 11.4344 0.0885 0.0625 0.4292 -0.1442 0.3372 9.6944 0.8259 12.0000 12.0000 11.2502 0.2237 0.3790 0.0999 11.1449 0.0825 0.0545 0.4181 -0.1521 0.3335 9.9463 0.7694 12.0000 12.0000 11.2419 0.1899 0.3701 0.0999 10.8695 0.0769 0.0473 0.4070 -0.1608 0.3292 10.1981 0.7159 12.0000 12.0000 11.2331 0.1567 0.3610 0.0999 10.6072 0.0715 0.0410 0.3958 -0.1701 0.3245 10.4398 0.6678 12.0000 12.0000 11.2232 0.1254 0.3523 0.0999 10.3671 0.0667 0.0357 0.3852 -0.1799 0.3194 10.5056 0.6554 12.0000 12.0000 11.2201 0.1170 0.3499 0.0999 10.3036 0.0655 0.0344 0.3823 -0.1827 0.3179 10.5611 0.6449 12.0000 12.0000 11.2021 0.1098 0.3479 0.0999 10.2505 0.0644 0.0333 0.3795 -0.1851 0.3164 10.6167 0.6296 12.0000 12.0000 11.1562 0.0977 0.3449 0.0999 10.1980 0.0629 0.0318 0.3753 -0.1903 0.3137 10.6722 0.6067 12.0000 12.0000 11.0816 0.0780 0.3406 0.0999 10.1460 0.0606 0.0295 0.3690 -0.1996 0.3097 10.7278 0.5750 12.0000 12.0000 10.9971 0.0494 0.3347 0.0999 10.0946 0.0575 0.0266 0.3604 -0.2139 0.3042 10.7833 0.5323 12.0000 12.0000 10.8912 0.0098 0.3268 0.0999 10.0436 0.0532 0.0228 0.3494 -0.2344 0.2971 10.8389 0.4740 12.0000 12.0000 10.4508 -0.0453 0.3163 0.1000 9.9932 0.0474 0.0181 0.3350 -0.2632 0.2882 10.8944 0.3883 12.0000 12.0000 9.9782 -0.1277 0.3011 0.1000 9.9432 0.0388 0.0122 0.3151 -0.3070 0.2763 10.9500 0.2195 12.0000 12.0000 10.4401 -0.2920 0.2717 0.1000 9.8938 0.0220 0.0040 0.2788 -0.3954 0.2562 11.0000 0.0286 12.0000 12.0061 12.0060 -0.4786 0.2388 0.1000 9.8546 0.0029 0.0000 0.2388 0.0000 0.0000 RADIUS: 11.00 PROPELLER RADIUS (IN) HUBRAD: 0.69 HUB RADIUS (IN) HUBTRA: 2.86 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.302313 TOTAL WEIGHT (Kg) = 0.137103 TOTAL VOLUME (IN**3) = 4.925065 TOTAL PROJECTED AREA (IN**2) = 27.9595 MOMENT OF INERTIA (SNAIL-IN**2) = 0.016519 MOMENT OF INERTIA (Kg-M**2) = 0.001866 STATIC MOMENT, ONE SIDE (IN-LB) = 0.562601 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 = 73.217 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5283.94 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.86, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.34, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412