11x12W (11x12W.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 1.0000 0.7500 0.0000 0.0000 0.5000 0.0000 0.4924 0.0000 0.4924 0.0000 0.0450 0.0000 0.0000 0.1250 0.9573 1.8469 0.0169 -0.7193 0.4944 0.0070 0.4624 1.2330 0.4426 0.4023 0.0527 0.0089 -0.1819 0.2500 0.9086 2.8875 0.1322 -1.3987 0.4900 0.0261 0.4337 4.8121 0.3940 0.3955 0.0738 0.0307 -0.1741 0.3750 0.8626 3.8719 0.4371 -1.8947 0.4873 0.0542 0.4063 10.5086 0.3505 0.3815 0.1048 0.0567 -0.1597 0.5000 0.8289 4.8000 1.0151 -2.0534 0.4862 0.0887 0.3801 17.9069 0.3151 0.3598 0.1425 0.0855 -0.1399 0.6250 0.8142 5.6719 1.9351 -1.7402 0.4870 0.1267 0.3553 26.2322 0.2892 0.3328 0.1838 0.1158 -0.1164 0.7500 0.8197 6.4875 3.2299 -0.8589 0.4899 0.1656 0.3317 34.4269 0.2719 0.3030 0.2252 0.1463 -0.0910 0.8750 0.8402 7.2469 4.8616 0.6002 0.4951 0.2025 0.3093 41.4859 0.2599 0.2728 0.2636 0.1755 -0.0652 1.0000 0.8656 7.9500 6.6752 2.4916 0.5026 0.2348 0.2883 46.7326 0.2495 0.2441 0.2957 0.2022 -0.0406 1.1250 0.8848 8.5969 8.3636 4.4499 0.5127 0.2597 0.2685 49.7969 0.2376 0.2180 0.3181 0.2252 -0.0185 1.2500 0.8879 9.1875 9.4894 5.8910 0.5256 0.2745 0.2500 50.3867 0.2220 0.1949 0.3279 0.2434 -0.0002 1.3754 0.8806 9.7235 10.0524 6.7229 0.5408 0.2812 0.2327 49.3149 0.2049 0.1748 0.3284 0.2584 0.0138 1.5078 0.8782 10.2278 10.5755 7.5648 0.5582 0.2862 0.2159 48.1461 0.1896 0.1575 0.3278 0.2734 0.0250 1.6405 0.8810 10.6703 11.0324 8.3640 0.5767 0.2890 0.2004 46.9451 0.1766 0.1433 0.3260 0.2873 0.0329 1.7733 0.8882 11.0494 11.4218 9.1043 0.5958 0.2898 0.1864 45.7108 0.1656 0.1317 0.3231 0.3001 0.0379 1.9060 0.8993 11.3650 11.7443 9.7734 0.6154 0.2888 0.1739 44.4405 0.1563 0.1221 0.3189 0.3116 0.0403 2.0388 0.9135 11.6171 12.0009 10.3607 0.6350 0.2859 0.1627 43.1320 0.1486 0.1142 0.3136 0.3216 0.0406 2.1716 0.9302 11.8058 12.1926 10.8569 0.6544 0.2813 0.1530 41.7841 0.1423 0.1081 0.3071 0.3295 0.0386 2.3043 0.9488 11.9311 12.3203 11.2546 0.6732 0.2750 0.1448 40.3958 0.1373 0.1036 0.2995 0.3351 0.0348 2.4371 0.9685 11.9929 12.3850 11.5476 0.6911 0.2670 0.1379 38.9664 0.1336 0.1006 0.2906 0.3387 0.0294 2.5698 0.9886 12.0000 12.3967 11.7398 0.7077 0.2574 0.1326 37.5154 0.1310 0.0989 0.2805 0.3404 0.0230 2.7026 1.0086 12.0000 12.4042 11.8757 0.7228 0.2461 0.1286 36.1475 0.1297 0.0984 0.2692 0.3411 0.0151 2.8353 1.0276 12.0000 12.4152 11.9620 0.7360 0.2332 0.1261 34.8725 0.1296 0.0991 0.2567 0.3412 0.0061 2.9681 1.0450 12.0000 12.4311 11.9987 0.7471 0.2187 0.1250 33.6864 0.1307 0.1011 0.2430 0.3406 -0.0040 3.1009 1.0602 12.0000 12.4509 12.0001 0.7556 0.2026 0.1250 32.5809 0.1325 0.1038 0.2281 0.3393 -0.0151 3.2336 1.0724 12.0000 12.4708 12.0002 0.7612 0.1853 0.1250 31.5414 0.1340 0.1060 0.2120 0.3367 -0.0270 3.3664 1.0809 12.0000 12.4903 12.0004 0.7637 0.1668 0.1250 30.5624 0.1351 0.1075 0.1947 0.3326 -0.0396 3.4991 1.0850 12.0000 12.5095 12.0004 0.7626 0.1473 0.1250 29.6391 0.1356 0.1082 0.1761 0.3269 -0.0527 3.6319 1.0841 12.0000 12.5283 12.0004 0.7578 0.1267 0.1250 28.7672 0.1355 0.1079 0.1564 0.3197 -0.0664 3.7647 1.0775 12.0000 12.5468 12.0004 0.7488 0.1050 0.1250 27.9427 0.1347 0.1065 0.1355 0.3109 -0.0805 3.8974 1.0643 12.0000 12.5647 12.0003 0.7353 0.0823 0.1250 27.1619 0.1330 0.1039 0.1133 0.3005 -0.0949 4.0302 1.0440 12.0000 12.5819 12.0003 0.7171 0.0587 0.1250 26.4215 0.1305 0.0999 0.0899 0.2885 -0.1096 4.1629 1.0158 12.0000 12.5984 12.0003 0.6937 0.0341 0.1250 25.7181 0.1270 0.0946 0.0653 0.2748 -0.1245 4.2957 0.9791 11.9976 12.6115 11.9978 0.6648 0.0087 0.1250 25.0446 0.1224 0.0878 0.0395 0.2594 -0.1395 4.4284 0.9330 11.9633 12.5912 11.9635 0.6302 -0.0177 0.1250 24.3476 0.1166 0.0798 0.0125 0.2421 -0.1543 4.5612 0.8770 11.8884 12.5282 11.8886 0.5896 -0.0450 0.1250 23.6124 0.1096 0.0705 -0.0158 0.2230 -0.1688 4.6940 0.8103 11.7729 12.4218 11.7731 0.5425 -0.0730 0.1250 22.8398 0.1013 0.0602 -0.0452 0.2020 -0.1830 4.8267 0.7323 11.6168 12.2711 11.6169 0.4886 -0.1019 0.1250 22.0294 0.0915 0.0493 -0.0759 0.1793 -0.1971 4.9595 0.6421 11.4201 12.0738 11.4202 0.4277 -0.1313 0.1250 21.1793 0.0803 0.0380 -0.1078 0.1548 -0.2112 5.0922 0.5392 11.1828 11.8257 11.1829 0.3594 -0.1614 0.1250 20.2846 0.0674 0.0269 -0.1409 0.1286 -0.2252 5.2195 0.4279 10.9171 11.5309 10.9172 0.2867 -0.1906 0.1250 19.3719 0.0535 0.0170 -0.1737 0.1019 -0.2389 5.2528 0.3966 10.8416 11.4423 10.8416 0.2665 -0.1983 0.1250 19.1210 0.0496 0.0146 -0.1825 0.0947 -0.2425 5.2806 0.3699 10.7765 11.3636 10.7766 0.2492 -0.2047 0.1250 18.9061 0.0462 0.0128 -0.1899 0.0886 -0.2455 5.3083 0.3425 10.7097 11.2799 10.7097 0.2316 -0.2112 0.1250 18.6852 0.0428 0.0110 -0.1973 0.0824 -0.2485 5.3361 0.3145 10.6411 11.1902 10.6411 0.2136 -0.2177 0.1250 18.4569 0.0393 0.0093 -0.2048 0.0762 -0.2516 5.3639 0.2858 10.5707 11.0932 10.5707 0.1953 -0.2241 0.1250 18.2191 0.0357 0.0077 -0.2124 0.0699 -0.2547 5.3917 0.2564 10.4985 10.9868 10.4985 0.1765 -0.2306 0.1250 17.9688 0.0321 0.0062 -0.2200 0.0635 -0.2578 5.4194 0.2238 10.4245 10.8680 10.4249 0.1549 -0.2379 0.1250 17.7012 0.0280 0.0048 -0.2285 0.0557 -0.2614 5.4472 0.1805 10.3488 10.7316 10.3696 0.1234 -0.2481 0.1250 17.4089 0.0226 0.0031 -0.2405 0.0427 -0.2670 5.4750 0.1126 10.2713 10.5672 10.5273 0.0686 -0.2653 0.1250 17.0760 0.0141 0.0012 -0.2605 0.0173 -0.2772 5.5000 0.0068 10.2000 10.2002 10.1999 -0.0234 -0.2931 0.1250 16.4448 0.0008 0.0000 -0.2931 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.25 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.098145 TOTAL WEIGHT (Kg) = 0.044510 TOTAL VOLUME (IN**3) = 1.598907 TOTAL PROJECTED AREA (IN**2) = 8.1278 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001285 MOMENT OF INERTIA (Kg-M**2) = 0.000145 STATIC MOMENT, ONE SIDE (IN-LB) = 0.085007 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 = 107.562 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12250.29 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.