6.5x7.5 (65x75.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 -3.1245 0.0000 0.0000 0.3250 0.0000 0.4385 0.0000 0.2850 0.0000 0.1000 0.0000 0.0000 0.0900 0.6200 -1.8878 0.0095 -0.3246 0.3209 0.0074 0.4368 0.9631 0.2708 0.1499 0.1065 0.0094 -0.0343 0.1800 0.5863 -0.7276 0.0752 -0.6354 0.3176 0.0275 0.4319 3.8047 0.2532 0.1468 0.1238 0.0235 -0.0236 0.2700 0.5537 0.3561 0.2527 -0.8531 0.3150 0.0567 0.4236 8.4710 0.2346 0.1421 0.1492 0.0387 -0.0067 0.3600 0.5272 1.3633 0.5952 -0.8874 0.3129 0.0917 0.4121 14.7416 0.2173 0.1354 0.1795 0.0541 0.0141 0.4500 0.5114 2.2940 1.1478 -0.6575 0.3113 0.1293 0.3973 22.0941 0.2032 0.1274 0.2114 0.0690 0.0363 0.5400 0.5087 3.1482 1.9340 -0.1035 0.3099 0.1664 0.3792 29.6831 0.1929 0.1186 0.2418 0.0825 0.0572 0.6300 0.5179 3.9259 2.9337 0.7854 0.3088 0.1998 0.3577 36.5435 0.1853 0.1098 0.2675 0.0935 0.0745 0.7200 0.5355 4.6271 4.0575 1.9332 0.3078 0.2262 0.3330 41.8892 0.1783 0.1016 0.2856 0.1010 0.0860 0.8100 0.5564 5.2519 5.1326 3.1487 0.3068 0.2425 0.3050 45.2423 0.1697 0.0941 0.2935 0.1038 0.0897 0.9000 0.5760 5.8001 5.9260 4.1394 0.3057 0.2455 0.2740 46.3414 0.1578 0.0875 0.2886 0.1013 0.0837 0.9891 0.5908 6.2674 6.4120 4.8312 0.3042 0.2387 0.2458 45.8960 0.1452 0.0807 0.2753 0.0957 0.0724 1.0623 0.5988 6.5955 6.7509 5.3606 0.3028 0.2323 0.2264 45.3246 0.1356 0.0746 0.2645 0.0913 0.0646 1.1347 0.6029 6.8697 7.0337 5.8395 0.3011 0.2252 0.2105 44.6134 0.1269 0.0686 0.2538 0.0871 0.0580 1.2070 0.6033 7.0946 7.2661 6.2658 0.2992 0.2173 0.1979 43.7747 0.1194 0.0629 0.2433 0.0832 0.0527 1.2793 0.5999 7.2700 7.4491 6.6318 0.2970 0.2088 0.1886 42.8220 0.1131 0.0576 0.2328 0.0797 0.0484 1.3516 0.5927 7.3961 7.5841 6.9310 0.2945 0.1996 0.1825 41.7656 0.1082 0.0529 0.2224 0.0769 0.0453 1.4240 0.5819 7.4727 7.6719 7.1580 0.2918 0.1898 0.1796 40.6125 0.1045 0.0488 0.2121 0.0747 0.0431 1.4963 0.5697 7.4999 7.7108 7.3088 0.2888 0.1799 0.1777 39.3575 0.1013 0.0453 0.2020 0.0728 0.0413 1.5686 0.5572 7.5000 7.7219 7.4024 0.2854 0.1700 0.1759 38.0778 0.0980 0.0421 0.1919 0.0711 0.0394 1.6409 0.5444 7.5000 7.7324 7.4647 0.2818 0.1603 0.1740 36.8686 0.0947 0.0392 0.1819 0.0697 0.0372 1.7133 0.5312 7.5000 7.7425 7.4960 0.2779 0.1506 0.1721 35.7253 0.0914 0.0367 0.1719 0.0687 0.0345 1.7856 0.5177 7.5000 7.7522 7.5000 0.2737 0.1412 0.1702 34.6433 0.0881 0.0344 0.1621 0.0679 0.0316 1.8579 0.5039 7.5000 7.7614 7.5002 0.2691 0.1318 0.1683 33.6184 0.0848 0.0322 0.1524 0.0672 0.0285 1.9303 0.4897 7.5000 7.7702 7.5004 0.2642 0.1226 0.1664 32.6465 0.0815 0.0300 0.1427 0.0666 0.0252 2.0026 0.4752 7.5000 7.7785 7.5006 0.2590 0.1135 0.1646 31.7240 0.0782 0.0279 0.1331 0.0659 0.0218 2.0749 0.4604 7.5000 7.7863 7.5006 0.2535 0.1045 0.1627 30.8473 0.0749 0.0259 0.1236 0.0652 0.0183 2.1472 0.4453 7.5000 7.7935 7.5005 0.2476 0.0956 0.1608 30.0133 0.0716 0.0239 0.1143 0.0644 0.0146 2.2196 0.4298 7.5000 7.8001 7.5005 0.2413 0.0869 0.1589 29.2188 0.0683 0.0220 0.1050 0.0636 0.0109 2.2919 0.4141 7.5000 7.8061 7.5005 0.2347 0.0783 0.1570 28.4610 0.0650 0.0202 0.0957 0.0627 0.0071 2.3642 0.3980 7.5000 7.8113 7.5004 0.2277 0.0698 0.1551 27.7373 0.0617 0.0184 0.0866 0.0616 0.0032 2.4366 0.3816 7.5000 7.8157 7.5004 0.2204 0.0614 0.1533 27.0451 0.0585 0.0167 0.0776 0.0604 -0.0008 2.5089 0.3649 7.5000 7.8190 7.5004 0.2127 0.0532 0.1514 26.3820 0.0552 0.0151 0.0686 0.0591 -0.0048 2.5812 0.3479 7.5000 7.8213 7.5003 0.2046 0.0450 0.1495 25.7458 0.0520 0.0136 0.0597 0.0575 -0.0089 2.6535 0.3306 7.5000 7.8222 7.5003 0.1960 0.0370 0.1476 25.1342 0.0488 0.0121 0.0509 0.0558 -0.0130 2.7259 0.3130 7.5000 7.8215 7.5002 0.1871 0.0290 0.1457 24.5451 0.0456 0.0107 0.0422 0.0539 -0.0172 2.7982 0.2950 7.4907 7.8097 7.4909 0.1778 0.0212 0.1438 23.9509 0.0424 0.0094 0.0336 0.0517 -0.0213 2.8705 0.2768 7.4419 7.7561 7.4421 0.1681 0.0134 0.1420 23.2693 0.0393 0.0082 0.0250 0.0492 -0.0254 2.9428 0.2582 7.3512 7.6578 7.3514 0.1580 0.0056 0.1401 22.4968 0.0362 0.0071 0.0165 0.0464 -0.0293 3.0152 0.2394 7.2187 7.5142 7.2188 0.1474 -0.0020 0.1382 21.6351 0.0331 0.0060 0.0081 0.0433 -0.0332 3.0846 0.2210 7.0522 7.3332 7.0523 0.1369 -0.0093 0.1364 20.7252 0.0301 0.0051 0.0002 0.0401 -0.0368 3.1039 0.2158 6.9990 7.2751 6.9990 0.1338 -0.0113 0.1359 20.4573 0.0293 0.0048 -0.0020 0.0392 -0.0378 3.1203 0.2113 6.9514 7.2231 6.9515 0.1312 -0.0131 0.1354 20.2249 0.0286 0.0046 -0.0039 0.0383 -0.0387 3.1367 0.2053 6.9017 7.1690 6.9021 0.1271 -0.0153 0.1350 19.9887 0.0277 0.0043 -0.0064 0.0367 -0.0399 3.1532 0.1968 6.8499 7.1126 6.8508 0.1207 -0.0184 0.1346 19.7486 0.0265 0.0040 -0.0098 0.0339 -0.0417 3.1696 0.1856 6.7958 7.0540 6.8000 0.1117 -0.0223 0.1342 19.5044 0.0249 0.0035 -0.0142 0.0296 -0.0440 3.1860 0.1709 6.7397 6.9929 6.7658 0.0993 -0.0273 0.1337 19.2559 0.0229 0.0030 -0.0198 0.0235 -0.0471 3.2024 0.1513 6.6813 6.9294 6.7469 0.0823 -0.0338 0.1333 19.0027 0.0202 0.0023 -0.0271 0.0149 -0.0511 3.2188 0.1229 6.6209 6.8633 6.7721 0.0568 -0.0430 0.1329 18.7449 0.0163 0.0016 -0.0376 0.0017 -0.0570 3.2352 0.0682 6.5582 6.7958 7.0952 0.0064 -0.0603 0.1325 18.4857 0.0090 0.0005 -0.0573 -0.0250 -0.0683 3.2500 0.0088 6.5000 6.5000 6.5000 -0.0487 -0.0788 0.1321 17.6568 0.0012 0.0000 -0.0788 0.0000 0.0000 RADIUS: 3.25 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.90 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.022716 TOTAL WEIGHT (Kg) = 0.010302 TOTAL VOLUME (IN**3) = 0.370075 TOTAL PROJECTED AREA (IN**2) = 2.5558 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000075 MOMENT OF INERTIA (Kg-M**2) = 0.000008 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009996 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 = 80.280 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 49385.79 BASED ON MODULUS (MILLION) = 2.80 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.