20x12 (20x12.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 1.7500 5.0509 0.0000 0.0000 0.8750 0.0000 0.3169 0.0000 0.5546 0.0000 0.3500 0.0000 0.0000 0.2842 1.6713 6.0121 0.0342 -0.5514 0.8638 0.0223 0.3063 1.0977 0.5119 0.8909 0.3661 0.0304 0.0432 0.5684 1.6082 6.8822 0.2605 -0.9649 0.8578 0.0816 0.2960 4.1719 0.4761 0.8730 0.4075 0.0592 0.0662 0.8526 1.5665 7.6656 0.8300 -1.0048 0.8562 0.1675 0.2862 8.8072 0.4483 0.8444 0.4668 0.0877 0.1024 1.1368 1.5513 8.3670 1.8350 -0.5069 0.8578 0.2701 0.2767 14.4081 0.4292 0.8083 0.5376 0.1151 0.1476 1.4210 1.5630 8.9906 3.2929 0.5979 0.8619 0.3795 0.2676 20.2448 0.4182 0.7669 0.6132 0.1407 0.1978 1.7052 1.5960 9.5410 5.1355 2.2671 0.8674 0.4857 0.2588 25.6096 0.4131 0.7222 0.6866 0.1639 0.2487 1.9894 1.6389 10.0226 7.2045 4.3378 0.8733 0.5786 0.2504 29.9578 0.4104 0.6754 0.7502 0.1840 0.2958 2.2736 1.6774 10.4398 9.2535 6.5273 0.8787 0.6483 0.2424 32.9336 0.4066 0.6275 0.7961 0.2006 0.3341 2.5578 1.6969 10.7972 10.9562 8.4410 0.8827 0.6849 0.2348 34.2835 0.3984 0.5796 0.8157 0.2128 0.3585 2.8420 1.6854 11.0991 11.9166 9.5863 0.8842 0.6784 0.2275 33.7169 0.3835 0.5324 0.8005 0.2198 0.3631 3.1228 1.6516 11.3474 12.2191 10.0158 0.8837 0.6427 0.2207 31.9124 0.3645 0.4873 0.7617 0.2241 0.3533 3.3460 1.6233 11.5120 12.4199 10.3313 0.8830 0.6149 0.2156 30.5730 0.3499 0.4532 0.7313 0.2287 0.3448 3.5658 1.5943 11.6482 12.5899 10.6219 0.8819 0.5880 0.2107 29.3333 0.3359 0.4214 0.7017 0.2341 0.3360 3.7856 1.5643 11.7607 12.7346 10.8908 0.8804 0.5616 0.2061 28.1645 0.3224 0.3913 0.6727 0.2402 0.3268 4.0053 1.5332 11.8515 12.8564 11.1357 0.8785 0.5358 0.2017 27.0605 0.3092 0.3630 0.6441 0.2470 0.3171 4.2251 1.5012 11.9227 12.9574 11.3550 0.8761 0.5104 0.1975 26.0164 0.2965 0.3366 0.6160 0.2542 0.3069 4.4449 1.4682 11.9765 13.0399 11.5469 0.8732 0.4855 0.1935 25.0281 0.2842 0.3119 0.5884 0.2618 0.2962 4.6647 1.4343 12.0147 13.1061 11.7097 0.8697 0.4611 0.1898 24.0926 0.2722 0.2889 0.5613 0.2697 0.2852 4.8845 1.3994 12.0396 13.1583 11.8421 0.8656 0.4371 0.1863 23.2070 0.2607 0.2676 0.5346 0.2778 0.2737 5.1043 1.3637 12.0531 13.1987 11.9429 0.8608 0.4136 0.1830 22.3693 0.2495 0.2479 0.5083 0.2860 0.2618 5.3241 1.3271 12.0573 13.2295 12.0110 0.8553 0.3905 0.1799 21.5776 0.2388 0.2297 0.4826 0.2942 0.2496 5.5438 1.2896 12.0543 13.2530 12.0455 0.8491 0.3679 0.1771 20.8305 0.2283 0.2128 0.4572 0.3023 0.2370 5.7636 1.2512 12.0461 13.2715 12.0462 0.8421 0.3458 0.1744 20.1265 0.2183 0.1972 0.4324 0.3103 0.2241 5.9834 1.2121 12.0349 13.2860 12.0349 0.8343 0.3242 0.1719 19.4633 0.2083 0.1823 0.4080 0.3181 0.2112 6.2032 1.1721 12.0226 13.2983 12.0227 0.8256 0.3032 0.1693 18.8392 0.1984 0.1679 0.3841 0.3255 0.1983 6.4230 1.1313 12.0113 13.3103 12.0114 0.8159 0.2828 0.1667 18.2534 0.1886 0.1541 0.3606 0.3324 0.1855 6.6428 1.0897 12.0031 13.3242 12.0031 0.8053 0.2630 0.1642 17.7050 0.1789 0.1408 0.3376 0.3389 0.1728 6.8626 1.0473 12.0000 13.3419 12.0000 0.7937 0.2439 0.1616 17.1933 0.1693 0.1280 0.3151 0.3449 0.1602 7.0824 1.0041 12.0000 13.3614 11.9999 0.7810 0.2252 0.1590 16.7128 0.1597 0.1158 0.2930 0.3502 0.1478 7.3021 0.9602 12.0000 13.3795 11.9999 0.7673 0.2071 0.1565 16.2575 0.1503 0.1042 0.2714 0.3548 0.1355 7.5219 0.9156 12.0000 13.3961 11.9999 0.7523 0.1895 0.1539 15.8251 0.1409 0.0932 0.2503 0.3587 0.1234 7.7417 0.8702 12.0000 13.4113 11.9998 0.7362 0.1724 0.1514 15.4141 0.1317 0.0828 0.2296 0.3617 0.1115 7.9615 0.8241 12.0000 13.4249 11.9998 0.7189 0.1558 0.1488 15.0226 0.1226 0.0730 0.2093 0.3639 0.0999 8.1813 0.7773 12.0000 13.4369 11.9998 0.7003 0.1397 0.1462 14.6491 0.1137 0.0639 0.1896 0.3652 0.0885 8.4011 0.7298 12.0000 13.4473 11.9998 0.6803 0.1241 0.1437 14.2923 0.1048 0.0553 0.1703 0.3655 0.0773 8.6209 0.6816 12.0000 13.4559 11.9998 0.6590 0.1089 0.1411 13.9509 0.0962 0.0474 0.1514 0.3647 0.0663 8.8406 0.6328 12.0000 13.4627 11.9999 0.6363 0.0941 0.1385 13.6237 0.0877 0.0401 0.1330 0.3629 0.0556 9.0604 0.5833 12.0000 13.4674 11.9999 0.6121 0.0798 0.1360 13.3096 0.0793 0.0335 0.1151 0.3599 0.0452 9.2802 0.5331 12.0000 13.4736 11.9984 0.5864 0.0659 0.1334 13.0111 0.0711 0.0274 0.0976 0.3557 0.0350 9.4912 0.4849 12.0000 13.7713 11.9221 0.5603 0.0553 0.1309 13.0032 0.0635 0.0222 0.0821 0.3506 0.0255 9.5505 0.4714 12.0000 13.9515 11.8931 0.5527 0.0530 0.1302 13.0885 0.0614 0.0209 0.0782 0.3489 0.0230 9.6010 0.4599 12.0000 14.1428 11.8706 0.5461 0.0513 0.1297 13.1943 0.0596 0.0198 0.0750 0.3474 0.0209 9.6515 0.4484 12.0000 14.3711 11.8522 0.5395 0.0498 0.1291 13.3321 0.0579 0.0187 0.0719 0.3458 0.0189 9.7020 0.4369 12.0000 14.6383 11.8399 0.5327 0.0485 0.1285 13.5028 0.0561 0.0176 0.0690 0.3442 0.0169 9.7525 0.4228 12.0000 14.9471 11.8367 0.5234 0.0467 0.1279 13.7083 0.0541 0.0164 0.0655 0.3411 0.0146 9.8030 0.3988 12.0000 15.3010 11.8472 0.5043 0.0428 0.1273 13.9508 0.0508 0.0145 0.0594 0.3325 0.0107 9.8535 0.3621 12.0000 15.7015 11.8854 0.4728 0.0357 0.1267 14.2308 0.0459 0.0119 0.0498 0.3170 0.0049 9.9040 0.3059 12.0000 16.1488 11.9536 0.4224 0.0236 0.1261 14.5478 0.0386 0.0084 0.0346 0.2910 -0.0041 9.9545 0.1981 12.0000 16.6470 12.1308 0.3223 -0.0023 0.1255 14.9040 0.0249 0.0035 0.0043 0.2371 -0.0213 10.0000 0.0181 12.0000 12.0000 12.0000 0.1527 -0.0496 0.1250 10.8125 0.0023 0.0000 -0.0496 0.0000 0.0000 RADIUS: 10.00 PROPELLER RADIUS (IN) HUBRAD: 0.88 HUB RADIUS (IN) HUBTRA: 2.84 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.427033 TOTAL WEIGHT (Kg) = 0.193666 TOTAL VOLUME (IN**3) = 6.956921 TOTAL PROJECTED AREA (IN**2) = 22.9382 MOMENT OF INERTIA (SNAIL-IN**2) = 0.012967 MOMENT OF INERTIA (Kg-M**2) = 0.001464 STATIC MOMENT, ONE SIDE (IN-LB) = 0.576321 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 = 62.154 INNER LIMIT (NORMALIZED BY RADIUS) = 0.087 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13678.16 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 4.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.