22x12WE (22x12WE.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 0.3527 0.0000 0.4850 0.0000 0.2450 0.0000 0.0000 0.3120 1.2956 12.0000 0.0441 -0.6911 0.6776 0.0219 0.3485 1.2896 0.4515 0.5400 0.2601 0.0303 0.0100 0.6240 1.2468 12.0000 0.3399 -1.1599 0.6778 0.0804 0.3356 4.9541 0.4185 0.5184 0.2983 0.0590 0.0341 0.9360 1.2340 12.0000 1.0778 -1.0371 0.6864 0.1660 0.3142 10.3855 0.3878 0.4906 0.3537 0.0857 0.0721 1.2480 1.2610 12.0000 2.3396 -0.1068 0.7017 0.2690 0.2845 16.6133 0.3587 0.4600 0.4215 0.1093 0.1203 1.5600 1.3255 12.0000 4.0754 1.6428 0.7218 0.3801 0.2542 22.5769 0.3370 0.4282 0.4966 0.1295 0.1755 1.8720 1.4188 12.0000 6.1164 4.0236 0.7452 0.4898 0.2274 27.4750 0.3227 0.3965 0.5733 0.1459 0.2340 2.1840 1.5279 12.0000 8.2123 6.5499 0.7700 0.5885 0.2040 30.8987 0.3117 0.3658 0.6449 0.1582 0.2919 2.4960 1.6390 12.0000 10.0767 8.7856 0.7945 0.6670 0.1836 32.7219 0.3010 0.3382 0.7041 0.1654 0.3441 2.8080 1.7400 12.0000 11.4246 10.4429 0.8170 0.7156 0.1662 32.9246 0.2892 0.3164 0.7424 0.1651 0.3835 3.1200 1.8219 12.0000 11.9949 11.2373 0.8356 0.7250 0.1514 31.4613 0.2759 0.3052 0.7499 0.1522 0.4008 3.4283 1.8835 12.0000 12.0000 11.3736 0.8490 0.7069 0.1393 29.1212 0.2624 0.3027 0.7355 0.1284 0.3998 3.6740 1.9223 12.0000 12.0000 11.4595 0.8561 0.6919 0.1313 27.4668 0.2523 0.3009 0.7240 0.1095 0.3979 3.9160 1.9521 12.0000 12.0000 11.5286 0.8600 0.6769 0.1246 25.9988 0.2433 0.2996 0.7126 0.0907 0.3949 4.1580 1.9739 12.0000 12.0000 11.5820 0.8611 0.6616 0.1192 24.6703 0.2353 0.2988 0.7012 0.0718 0.3910 4.4000 1.9881 12.0000 12.0000 11.6189 0.8594 0.6462 0.1149 23.4637 0.2284 0.2987 0.6898 0.0532 0.3864 4.6420 1.9950 12.0000 12.0000 11.6391 0.8551 0.6306 0.1116 22.3637 0.2226 0.2991 0.6783 0.0350 0.3812 4.8840 1.9950 12.0000 12.0000 11.6416 0.8483 0.6151 0.1091 21.3577 0.2177 0.2998 0.6670 0.0175 0.3758 5.1260 1.9885 12.0000 12.0000 11.6258 0.8391 0.5997 0.1075 20.4345 0.2138 0.3005 0.6556 0.0010 0.3704 5.3680 1.9758 12.0000 12.0000 11.5895 0.8275 0.5846 0.1066 19.5848 0.2106 0.3005 0.6443 -0.0142 0.3652 5.6100 1.9573 12.0000 12.0000 11.5480 0.8138 0.5700 0.1058 18.8005 0.2070 0.2986 0.6329 -0.0283 0.3606 5.8520 1.9334 12.0000 12.0000 11.5035 0.7981 0.5560 0.1050 18.0746 0.2030 0.2944 0.6215 -0.0408 0.3566 6.0940 1.9044 12.0000 12.0000 11.4607 0.7804 0.5427 0.1043 17.4010 0.1985 0.2879 0.6102 -0.0519 0.3535 6.3360 1.8707 12.0000 12.0000 11.4211 0.7609 0.5300 0.1036 16.7744 0.1938 0.2792 0.5988 -0.0615 0.3511 6.5780 1.8327 12.0000 12.0000 11.3869 0.7397 0.5179 0.1029 16.1901 0.1887 0.2685 0.5874 -0.0697 0.3496 6.8200 1.7907 12.0000 12.0000 11.3588 0.7168 0.5065 0.1024 15.6443 0.1833 0.2560 0.5760 -0.0764 0.3488 7.0620 1.7451 12.0000 12.0000 11.3371 0.6925 0.4955 0.1018 15.1332 0.1777 0.2423 0.5646 -0.0821 0.3485 7.3040 1.6963 12.0000 12.0000 11.3162 0.6668 0.4847 0.1014 14.6537 0.1719 0.2281 0.5532 -0.0874 0.3481 7.5460 1.6447 12.0000 12.0000 11.2954 0.6399 0.4742 0.1009 14.2031 0.1660 0.2138 0.5418 -0.0925 0.3473 7.7880 1.5905 12.0000 12.0000 11.2748 0.6118 0.4639 0.1005 13.7788 0.1599 0.1994 0.5304 -0.0975 0.3463 8.0300 1.5342 12.0000 12.0000 11.2544 0.5828 0.4538 0.1002 13.3787 0.1537 0.1851 0.5191 -0.1024 0.3450 8.2720 1.4761 12.0000 12.0000 11.2340 0.5528 0.4439 0.0999 13.0008 0.1475 0.1710 0.5077 -0.1073 0.3434 8.5140 1.4167 12.0000 12.0000 11.2137 0.5220 0.4341 0.0997 12.6433 0.1412 0.1573 0.4963 -0.1123 0.3415 8.7560 1.3562 12.0000 12.0000 11.1934 0.4905 0.4244 0.0995 12.3046 0.1349 0.1440 0.4849 -0.1174 0.3394 8.9980 1.2950 12.0000 12.0000 11.1732 0.4585 0.4149 0.0993 11.9834 0.1286 0.1312 0.4735 -0.1226 0.3368 9.2400 1.2336 12.0000 12.0000 11.1529 0.4260 0.4055 0.0992 11.6783 0.1224 0.1190 0.4621 -0.1281 0.3340 9.4820 1.1722 12.0000 12.0000 11.1323 0.3932 0.3962 0.0992 11.3881 0.1163 0.1075 0.4508 -0.1338 0.3308 9.7240 1.1113 12.0000 12.0000 11.1114 0.3602 0.3869 0.0992 11.1118 0.1102 0.0966 0.4394 -0.1398 0.3273 9.9660 1.0512 12.0000 12.0000 11.0901 0.3271 0.3777 0.0992 10.8485 0.1043 0.0865 0.4280 -0.1463 0.3234 10.2080 0.9922 12.0000 12.0000 11.0682 0.2939 0.3685 0.0993 10.5972 0.0986 0.0771 0.4166 -0.1532 0.3192 10.4403 0.9318 12.0000 12.0000 11.0464 0.2571 0.3587 0.0995 10.3666 0.0927 0.0681 0.4045 -0.1630 0.3141 10.5056 0.9040 12.0000 12.0000 11.0400 0.2359 0.3540 0.0995 10.3036 0.0900 0.0642 0.3985 -0.1718 0.3111 10.5611 0.8741 12.0000 12.0000 11.0240 0.2115 0.3489 0.0996 10.2505 0.0870 0.0600 0.3917 -0.1828 0.3074 10.6167 0.8375 12.0000 12.0000 10.9886 0.1805 0.3426 0.0996 10.1980 0.0834 0.0551 0.3829 -0.1974 0.3022 10.6722 0.7932 12.0000 12.0000 10.9296 0.1417 0.3349 0.0997 10.1460 0.0790 0.0495 0.3720 -0.2165 0.2955 10.7278 0.7389 12.0000 12.0000 10.8451 0.0932 0.3255 0.0997 10.0946 0.0737 0.0430 0.3586 -0.2409 0.2873 10.7833 0.6713 12.0000 12.0000 10.7364 0.0313 0.3139 0.0998 10.0436 0.0670 0.0356 0.3423 -0.2726 0.2772 10.8389 0.5826 12.0000 12.0000 10.2214 -0.0515 0.2987 0.0998 9.9932 0.0582 0.0269 0.3215 -0.3159 0.2647 10.8944 0.4470 12.0000 12.0000 9.7863 -0.1806 0.2754 0.0999 9.9432 0.0446 0.0159 0.2915 -0.3846 0.2474 10.9500 0.2338 12.0000 12.0000 10.2917 -0.3863 0.2391 0.0999 9.8938 0.0234 0.0044 0.2467 -0.4953 0.2228 11.0000 0.0406 12.0000 12.0061 12.0061 -0.5729 0.2064 0.1000 9.8546 0.0041 0.0000 0.2064 0.0000 0.0000 RADIUS: 11.02 PROPELLER RADIUS (IN) HUBRAD: 0.69 HUB RADIUS (IN) HUBTRA: 3.12 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.368254 TOTAL WEIGHT (Kg) = 0.167009 TOTAL VOLUME (IN**3) = 5.999330 TOTAL PROJECTED AREA (IN**2) = 31.7891 MOMENT OF INERTIA (SNAIL-IN**2) = 0.023116 MOMENT OF INERTIA (Kg-M**2) = 0.002611 STATIC MOMENT, ONE SIDE (IN-LB) = 0.742778 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 = 92.210 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5088.84 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.13, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.91, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412