5.5x7.0 (55x70.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 0.6500 1.5537 0.0000 0.0000 0.3250 0.0000 0.4462 0.0000 0.2900 0.0000 0.1050 0.0000 0.0000 0.0700 0.6237 2.0774 0.0092 -0.2514 0.3197 0.0074 0.4446 1.2043 0.2773 0.1545 0.1113 0.0064 -0.0334 0.1400 0.5902 2.5747 0.0726 -0.4925 0.3114 0.0276 0.4399 4.7213 0.2596 0.1541 0.1281 0.0159 -0.0263 0.2100 0.5561 3.0455 0.2427 -0.6694 0.3011 0.0571 0.4322 10.4229 0.2403 0.1526 0.1530 0.0246 -0.0135 0.2800 0.5287 3.4898 0.5717 -0.6715 0.2896 0.0927 0.4213 18.0034 0.2228 0.1468 0.1832 0.0314 0.0061 0.3500 0.5138 3.9076 1.1087 -0.4035 0.2779 0.1313 0.4073 26.7553 0.2093 0.1374 0.2155 0.0374 0.0291 0.4200 0.5136 4.2990 1.8862 0.2158 0.2667 0.1698 0.3903 35.5549 0.2004 0.1258 0.2469 0.0430 0.0523 0.4900 0.5254 4.6639 2.8929 1.2185 0.2570 0.2051 0.3701 43.2177 0.1944 0.1132 0.2742 0.0480 0.0730 0.5600 0.5428 5.0023 4.0329 2.5273 0.2495 0.2343 0.3468 48.8966 0.1882 0.1007 0.2946 0.0518 0.0888 0.6300 0.5582 5.3143 5.0907 3.8916 0.2451 0.2541 0.3204 52.1323 0.1788 0.0890 0.3055 0.0541 0.0981 0.7000 0.5652 5.5998 5.7543 4.8894 0.2446 0.2616 0.2909 52.6080 0.1644 0.0781 0.3047 0.0550 0.1003 0.7697 0.5641 5.8576 6.0316 5.4266 0.2466 0.2596 0.2608 51.2788 0.1471 0.0673 0.2956 0.0562 0.0987 0.8335 0.5607 6.0710 6.2543 5.8415 0.2480 0.2556 0.2369 50.0577 0.1328 0.0586 0.2861 0.0576 0.0962 0.8971 0.5565 6.2614 6.4498 6.1742 0.2490 0.2495 0.2167 48.8501 0.1206 0.0515 0.2756 0.0586 0.0922 0.9606 0.5515 6.4300 6.6209 6.4189 0.2496 0.2413 0.2000 47.6474 0.1103 0.0460 0.2640 0.0592 0.0865 1.0241 0.5458 6.5767 6.7689 6.5768 0.2499 0.2311 0.1870 46.4494 0.1021 0.0420 0.2512 0.0597 0.0793 1.0877 0.5395 6.7017 6.8957 6.7019 0.2497 0.2194 0.1776 45.2572 0.0958 0.0389 0.2378 0.0597 0.0713 1.1512 0.5327 6.8049 7.0026 6.8053 0.2491 0.2072 0.1718 44.0718 0.0915 0.0366 0.2246 0.0592 0.0637 1.2147 0.5252 6.8862 7.0906 6.8868 0.2482 0.1946 0.1693 42.8925 0.0889 0.0350 0.2116 0.0583 0.0564 1.2783 0.5174 6.9457 7.1572 6.9465 0.2469 0.1821 0.1675 41.7049 0.0867 0.0336 0.1990 0.0573 0.0495 1.3418 0.5090 6.9835 7.2014 6.9843 0.2452 0.1698 0.1658 40.5031 0.0844 0.0322 0.1866 0.0561 0.0429 1.4053 0.5003 6.9994 7.2233 7.0002 0.2432 0.1579 0.1640 39.2845 0.0820 0.0307 0.1745 0.0549 0.0367 1.4689 0.4911 7.0000 7.2295 7.0007 0.2408 0.1461 0.1622 38.0724 0.0797 0.0293 0.1626 0.0536 0.0308 1.5324 0.4815 7.0000 7.2348 7.0006 0.2381 0.1347 0.1604 36.9211 0.0772 0.0278 0.1510 0.0525 0.0249 1.5959 0.4715 7.0000 7.2398 7.0006 0.2350 0.1235 0.1586 35.8288 0.0748 0.0264 0.1397 0.0514 0.0192 1.6595 0.4610 7.0000 7.2446 7.0006 0.2316 0.1127 0.1569 34.7918 0.0723 0.0249 0.1286 0.0503 0.0136 1.7230 0.4501 7.0000 7.2492 7.0005 0.2278 0.1021 0.1551 33.8065 0.0698 0.0235 0.1178 0.0493 0.0081 1.7866 0.4388 7.0000 7.2535 7.0005 0.2237 0.0918 0.1533 32.8695 0.0673 0.0221 0.1072 0.0483 0.0028 1.8501 0.4270 7.0000 7.2575 7.0005 0.2193 0.0819 0.1515 31.9777 0.0647 0.0207 0.0969 0.0474 -0.0025 1.9136 0.4148 7.0000 7.2612 7.0004 0.2145 0.0722 0.1498 31.1283 0.0621 0.0193 0.0868 0.0464 -0.0075 1.9772 0.4023 7.0000 7.2647 7.0004 0.2095 0.0628 0.1480 30.3184 0.0595 0.0179 0.0770 0.0455 -0.0125 2.0407 0.3892 7.0000 7.2678 7.0004 0.2041 0.0536 0.1462 29.5455 0.0569 0.0166 0.0675 0.0445 -0.0173 2.1042 0.3758 7.0000 7.2706 7.0003 0.1985 0.0448 0.1444 28.8073 0.0543 0.0153 0.0582 0.0435 -0.0220 2.1678 0.3620 7.0000 7.2730 7.0003 0.1925 0.0362 0.1426 28.1014 0.0516 0.0140 0.0492 0.0425 -0.0264 2.2313 0.3477 7.0000 7.2751 7.0003 0.1863 0.0280 0.1409 27.4258 0.0490 0.0128 0.0404 0.0415 -0.0308 2.2948 0.3330 7.0000 7.2768 7.0002 0.1797 0.0200 0.1391 26.7787 0.0463 0.0116 0.0319 0.0405 -0.0350 2.3584 0.3179 7.0000 7.2780 7.0002 0.1729 0.0123 0.1373 26.1582 0.0437 0.0104 0.0236 0.0394 -0.0390 2.4219 0.3024 7.0000 7.2787 7.0001 0.1658 0.0049 0.1355 25.5626 0.0410 0.0093 0.0156 0.0384 -0.0428 2.4854 0.2865 7.0000 7.2788 7.0001 0.1584 -0.0023 0.1338 24.9901 0.0383 0.0082 0.0078 0.0373 -0.0464 2.5490 0.2701 7.0000 7.2783 7.0001 0.1508 -0.0092 0.1320 24.4393 0.0357 0.0072 0.0003 0.0361 -0.0499 2.6099 0.2527 6.9991 7.2765 6.9995 0.1420 -0.0161 0.1303 23.9282 0.0329 0.0063 -0.0072 0.0343 -0.0534 2.6264 0.2449 6.9938 7.2713 6.9948 0.1368 -0.0191 0.1298 23.7798 0.0318 0.0059 -0.0105 0.0324 -0.0550 2.6403 0.2367 6.9856 7.2634 6.9874 0.1309 -0.0223 0.1294 23.6455 0.0306 0.0055 -0.0140 0.0299 -0.0568 2.6542 0.2266 6.9739 7.2521 6.9766 0.1233 -0.0262 0.1290 23.5027 0.0292 0.0050 -0.0183 0.0265 -0.0591 2.6681 0.2144 6.9588 7.2375 6.9698 0.1138 -0.0309 0.1286 23.3514 0.0276 0.0045 -0.0234 0.0220 -0.0618 2.6819 0.1995 6.9403 7.2194 6.9650 0.1017 -0.0365 0.1283 23.1914 0.0256 0.0039 -0.0295 0.0162 -0.0651 2.6958 0.1810 6.9184 7.1979 6.9638 0.0864 -0.0435 0.1279 23.0229 0.0232 0.0032 -0.0372 0.0086 -0.0693 2.7097 0.1569 6.8930 7.1730 6.9736 0.0658 -0.0526 0.1275 22.8458 0.0200 0.0024 -0.0471 -0.0019 -0.0749 2.7236 0.1201 6.8642 7.1452 7.0284 0.0335 -0.0664 0.1271 22.6620 0.0153 0.0014 -0.0622 -0.0188 -0.0835 2.7375 0.0627 6.8319 7.1154 7.3241 -0.0180 -0.0879 0.1267 22.4739 0.0079 0.0004 -0.0857 -0.0460 -0.0970 2.7500 0.0107 6.8000 6.8000 6.8000 -0.0647 -0.1071 0.1264 21.4820 0.0014 0.0000 -0.1071 0.0000 0.0000 RADIUS: 2.75 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.017640 TOTAL WEIGHT (Kg) = 0.008000 TOTAL VOLUME (IN**3) = 0.287372 TOTAL PROJECTED AREA (IN**2) = 2.0293 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000040 MOMENT OF INERTIA (Kg-M**2) = 0.000005 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006211 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 = 97.906 INNER LIMIT (NORMALIZED BY RADIUS) = 0.118 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 52733.21 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 2.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.