13.5x13.5 (135x135.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 1.1900 -9.0000 0.0000 0.0000 0.5950 0.0000 0.4454 0.0000 0.5300 0.0000 0.2000 0.0000 0.0000 0.2100 1.1258 -5.9602 0.0221 -0.7429 0.5867 0.0112 0.4407 0.9582 0.4962 0.5044 0.2080 0.0214 -0.0541 0.4200 1.0623 -3.1410 0.1742 -1.4255 0.5825 0.0414 0.4269 3.7770 0.4535 0.4810 0.2292 0.0504 -0.0413 0.6300 1.0060 -0.5423 0.5784 -1.8294 0.5820 0.0854 0.4037 8.3133 0.4062 0.4473 0.2597 0.0831 -0.0206 0.8400 0.9638 1.8360 1.3408 -1.7546 0.5851 0.1383 0.3736 14.2545 0.3601 0.4076 0.2959 0.1181 0.0052 1.0500 0.9410 3.9937 2.5360 -1.0422 0.5913 0.1953 0.3448 21.0263 0.3244 0.3658 0.3342 0.1537 0.0336 1.2600 0.9389 5.9310 4.1805 0.3885 0.6003 0.2516 0.3180 27.8364 0.2986 0.3252 0.3714 0.1884 0.0619 1.4700 0.9542 7.6477 6.2000 2.4866 0.6118 0.3023 0.2933 33.8722 0.2798 0.2879 0.4037 0.2209 0.0874 1.6800 0.9794 9.1440 8.3984 5.0170 0.6255 0.3426 0.2706 38.5065 0.2650 0.2557 0.4276 0.2496 0.1072 1.8900 1.0059 10.4197 10.4494 7.5341 0.6409 0.3677 0.2500 41.3455 0.2514 0.2294 0.4393 0.2732 0.1180 2.1000 1.0255 11.4750 11.9336 9.4218 0.6579 0.3727 0.2314 42.1269 0.2373 0.2098 0.4347 0.2901 0.1166 2.3064 1.0382 12.2974 12.7865 10.5535 0.6756 0.3627 0.2151 41.4230 0.2234 0.1958 0.4183 0.3008 0.1060 2.4515 1.0467 12.7478 13.2522 11.2360 0.6883 0.3540 0.2049 40.7075 0.2145 0.1875 0.4060 0.3065 0.0981 2.5929 1.0544 13.0857 13.6027 11.8042 0.7007 0.3443 0.1959 39.8597 0.2065 0.1801 0.3934 0.3110 0.0905 2.7344 1.0614 13.3236 13.8508 12.2678 0.7129 0.3335 0.1878 38.8753 0.1993 0.1731 0.3802 0.3152 0.0831 2.8759 1.0675 13.4615 13.9967 12.6199 0.7248 0.3217 0.1806 37.7613 0.1928 0.1660 0.3665 0.3193 0.0762 3.0173 1.0726 13.5000 14.0427 12.8551 0.7363 0.3088 0.1743 36.5277 0.1870 0.1591 0.3521 0.3235 0.0699 3.1588 1.0764 13.5000 14.0510 13.0275 0.7470 0.2948 0.1690 35.2968 0.1819 0.1528 0.3372 0.3280 0.0633 3.3003 1.0789 13.5000 14.0607 13.1732 0.7570 0.2799 0.1646 34.1403 0.1776 0.1474 0.3217 0.3326 0.0558 3.4417 1.0799 13.5000 14.0725 13.2921 0.7660 0.2641 0.1611 33.0542 0.1740 0.1427 0.3057 0.3372 0.0475 3.5832 1.0792 13.5000 14.0863 13.3842 0.7739 0.2475 0.1585 32.0331 0.1710 0.1387 0.2891 0.3417 0.0384 3.7247 1.0767 13.5000 14.0996 13.4496 0.7804 0.2305 0.1558 31.0680 0.1678 0.1348 0.2719 0.3461 0.0286 3.8661 1.0723 13.5000 14.1121 13.4882 0.7855 0.2130 0.1532 30.1543 0.1643 0.1308 0.2541 0.3502 0.0182 4.0076 1.0657 13.5000 14.1238 13.5000 0.7890 0.1950 0.1506 29.2883 0.1605 0.1268 0.2357 0.3539 0.0072 4.1491 1.0569 13.5000 14.1347 13.5002 0.7907 0.1766 0.1480 28.4664 0.1564 0.1225 0.2168 0.3571 -0.0042 4.2905 1.0457 13.5000 14.1447 13.5004 0.7905 0.1577 0.1454 27.6856 0.1520 0.1177 0.1972 0.3595 -0.0161 4.4320 1.0319 13.5000 14.1538 13.5006 0.7882 0.1385 0.1428 26.9429 0.1473 0.1125 0.1771 0.3611 -0.0284 4.5734 1.0154 13.5000 14.1620 13.5005 0.7837 0.1187 0.1402 26.2357 0.1423 0.1069 0.1564 0.3618 -0.0411 4.7149 0.9959 13.5000 14.1692 13.5005 0.7767 0.0986 0.1376 25.5614 0.1370 0.1009 0.1352 0.3614 -0.0541 4.8564 0.9734 13.5000 14.1754 13.5005 0.7672 0.0780 0.1350 24.9178 0.1314 0.0945 0.1133 0.3599 -0.0675 4.9978 0.9477 13.5000 14.1805 13.5004 0.7549 0.0569 0.1323 24.3027 0.1254 0.0879 0.0909 0.3572 -0.0812 5.1393 0.9187 13.5000 14.1844 13.5004 0.7398 0.0354 0.1297 23.7141 0.1192 0.0809 0.0679 0.3532 -0.0953 5.2808 0.8861 13.5000 14.1867 13.5003 0.7216 0.0134 0.1271 23.1499 0.1126 0.0738 0.0443 0.3477 -0.1097 5.4222 0.8498 13.5000 14.1874 13.5003 0.7003 -0.0090 0.1245 22.6084 0.1058 0.0665 0.0201 0.3407 -0.1244 5.5637 0.8096 13.4947 14.1809 13.4949 0.6756 -0.0319 0.1219 22.0804 0.0987 0.0591 -0.0046 0.3321 -0.1394 5.7052 0.7655 13.4454 14.1281 13.4456 0.6474 -0.0553 0.1193 21.5106 0.0913 0.0517 -0.0300 0.3216 -0.1545 5.8466 0.7172 13.3443 14.0205 13.3444 0.6155 -0.0793 0.1167 20.8899 0.0837 0.0445 -0.0559 0.3093 -0.1696 5.9881 0.6646 13.1912 13.8578 13.1913 0.5798 -0.1038 0.1141 20.2198 0.0758 0.0374 -0.0824 0.2950 -0.1849 6.1296 0.6054 12.9863 13.6384 12.9864 0.5402 -0.1288 0.1114 19.5002 0.0675 0.0304 -0.1095 0.2796 -0.2000 6.2710 0.5366 12.7295 13.3591 12.7296 0.4964 -0.1541 0.1088 18.7290 0.0584 0.0233 -0.1372 0.2643 -0.2149 6.4069 0.4613 12.4341 13.0306 12.4341 0.4504 -0.1788 0.1063 17.9365 0.0490 0.0169 -0.1643 0.2496 -0.2289 6.4466 0.4376 12.3387 12.9225 12.3388 0.4362 -0.1860 0.1056 17.6944 0.0462 0.0151 -0.1723 0.2453 -0.2330 6.4807 0.4166 12.2536 12.8248 12.2536 0.4237 -0.1923 0.1050 17.4821 0.0437 0.0137 -0.1793 0.2416 -0.2365 6.5148 0.3950 12.1654 12.7224 12.1655 0.4109 -0.1986 0.1043 17.2656 0.0412 0.0122 -0.1862 0.2379 -0.2401 6.5489 0.3728 12.0743 12.6149 12.0743 0.3979 -0.2049 0.1037 17.0443 0.0387 0.0109 -0.1932 0.2342 -0.2436 6.5830 0.3498 11.9801 12.5020 11.9801 0.3844 -0.2113 0.1031 16.8179 0.0361 0.0095 -0.2004 0.2303 -0.2472 6.6170 0.3212 11.8829 12.3836 11.8836 0.3658 -0.2191 0.1024 16.5864 0.0329 0.0080 -0.2091 0.2239 -0.2517 6.6511 0.2834 11.7827 12.2588 11.7985 0.3387 -0.2293 0.1018 16.3486 0.0289 0.0062 -0.2205 0.2130 -0.2578 6.6852 0.2313 11.6794 12.1263 11.7599 0.2981 -0.2432 0.1012 16.1029 0.0234 0.0041 -0.2361 0.1948 -0.2664 6.7193 0.1397 11.5732 11.9850 11.9626 0.2197 -0.2676 0.1006 15.8481 0.0140 0.0015 -0.2632 0.1562 -0.2817 6.7500 0.0115 11.4750 11.4751 11.4749 0.1052 -0.3011 0.1000 15.1398 0.0011 0.0000 -0.3011 0.0000 0.0000 RADIUS: 6.75 PROPELLER RADIUS (IN) HUBRAD: 0.60 HUB RADIUS (IN) HUBTRA: 2.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.154392 TOTAL WEIGHT (Kg) = 0.070019 TOTAL VOLUME (IN**3) = 2.515247 TOTAL PROJECTED AREA (IN**2) = 11.0433 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002621 MOMENT OF INERTIA (Kg-M**2) = 0.000296 STATIC MOMENT, ONE SIDE (IN-LB) = 0.153785 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 = 86.087 INNER LIMIT (NORMALIZED BY RADIUS) = 0.088 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 16816.96 BASED ON MODULUS (MILLION) = 2.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.10, 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.