10x10E (10x10E.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 0.8000 10.0000 0.0000 0.0000 0.4000 0.0000 0.3853 0.0000 0.3083 0.0000 0.0400 0.0000 0.0000 0.1200 0.7591 10.0000 0.0196 -0.4806 0.3947 0.0126 0.3504 1.4894 0.2660 0.1908 0.0515 0.0105 -0.0893 0.2400 0.7139 10.0000 0.1558 -0.9409 0.3907 0.0467 0.3185 5.9006 0.2274 0.1949 0.0823 0.0312 -0.0750 0.3600 0.6757 10.0000 0.5249 -1.1761 0.3883 0.0963 0.2896 13.0645 0.1957 0.1884 0.1245 0.0556 -0.0508 0.4800 0.6564 10.0000 1.2393 -0.9391 0.3875 0.1560 0.2634 22.3387 0.1729 0.1724 0.1753 0.0815 -0.0192 0.6000 0.6643 10.0000 2.3875 -0.0202 0.3883 0.2205 0.2399 32.3459 0.1593 0.1520 0.2325 0.1067 0.0165 0.7200 0.6992 10.0000 3.9868 1.6951 0.3908 0.2843 0.2188 41.3889 0.1530 0.1311 0.2916 0.1294 0.0532 0.8400 0.7529 10.0000 5.9149 4.0989 0.3950 0.3422 0.2001 48.2574 0.1507 0.1126 0.3469 0.1474 0.0877 0.9600 0.8140 10.0000 7.8590 6.5660 0.4010 0.3888 0.1837 52.4934 0.1495 0.0982 0.3921 0.1592 0.1169 1.0800 0.8718 10.0000 9.3611 8.5062 0.4088 0.4188 0.1693 54.0617 0.1476 0.0886 0.4215 0.1631 0.1371 1.2000 0.9193 10.0000 9.9946 9.3824 0.4184 0.4269 0.1569 52.9694 0.1442 0.0849 0.4296 0.1575 0.1440 1.3199 0.9554 10.0000 10.0000 9.4545 0.4283 0.4191 0.1462 50.3303 0.1397 0.0846 0.4223 0.1458 0.1409 1.4383 0.9841 10.0000 10.0000 9.5157 0.4360 0.4099 0.1374 47.8960 0.1352 0.0838 0.4138 0.1346 0.1382 1.5566 1.0066 10.0000 10.0000 9.5700 0.4418 0.3995 0.1300 45.6369 0.1309 0.0827 0.4042 0.1237 0.1353 1.6748 1.0231 10.0000 10.0000 9.6152 0.4457 0.3880 0.1240 43.5395 0.1269 0.0816 0.3936 0.1132 0.1319 1.7931 1.0340 10.0000 10.0000 9.6502 0.4479 0.3754 0.1192 41.5921 0.1233 0.0805 0.3821 0.1030 0.1280 1.9114 1.0396 10.0000 10.0000 9.6747 0.4483 0.3618 0.1155 39.7831 0.1201 0.0796 0.3696 0.0931 0.1232 2.0297 1.0402 10.0000 10.0000 9.6889 0.4471 0.3471 0.1127 38.1017 0.1173 0.0788 0.3565 0.0835 0.1174 2.1479 1.0361 10.0000 10.0000 9.6937 0.4443 0.3315 0.1108 36.5373 0.1148 0.0781 0.3425 0.0742 0.1108 2.2662 1.0275 10.0000 10.0000 9.6921 0.4401 0.3152 0.1095 35.0802 0.1125 0.0773 0.3279 0.0654 0.1034 2.3845 1.0149 10.0000 10.0000 9.6899 0.4344 0.2984 0.1084 33.7216 0.1100 0.0759 0.3127 0.0571 0.0956 2.5028 0.9986 10.0000 10.0000 9.6863 0.4274 0.2811 0.1073 32.4530 0.1072 0.0739 0.2970 0.0496 0.0876 2.6210 0.9787 10.0000 10.0000 9.6794 0.4191 0.2636 0.1064 31.2670 0.1041 0.0715 0.2808 0.0427 0.0795 2.7393 0.9557 10.0000 10.0000 9.6672 0.4096 0.2460 0.1054 30.1567 0.1008 0.0687 0.2643 0.0366 0.0714 2.8576 0.9299 10.0000 10.0000 9.6534 0.3991 0.2283 0.1046 29.1159 0.0972 0.0655 0.2476 0.0311 0.0634 2.9759 0.9015 10.0000 10.0000 9.6391 0.3874 0.2107 0.1038 28.1387 0.0935 0.0620 0.2307 0.0263 0.0554 3.0941 0.8709 10.0000 10.0000 9.6247 0.3748 0.1932 0.1030 27.2202 0.0897 0.0581 0.2136 0.0222 0.0475 3.2124 0.8383 10.0000 10.0000 9.6106 0.3613 0.1758 0.1024 26.3555 0.0858 0.0541 0.1965 0.0186 0.0398 3.3307 0.8042 10.0000 10.0000 9.5972 0.3470 0.1587 0.1017 25.5405 0.0818 0.0499 0.1793 0.0155 0.0322 3.4490 0.7687 10.0000 10.0000 9.5849 0.3320 0.1419 0.1012 24.7713 0.0778 0.0456 0.1623 0.0128 0.0247 3.5672 0.7322 10.0000 10.0000 9.5736 0.3163 0.1254 0.1007 24.0444 0.0738 0.0413 0.1454 0.0105 0.0174 3.6855 0.6951 10.0000 10.0000 9.5639 0.2999 0.1093 0.1003 23.3566 0.0697 0.0372 0.1288 0.0084 0.0101 3.8038 0.6576 10.0000 10.0000 9.5542 0.2831 0.0935 0.1000 22.7050 0.0657 0.0332 0.1124 0.0062 0.0028 3.9221 0.6200 10.0000 10.0000 9.5440 0.2658 0.0782 0.0997 22.0870 0.0618 0.0294 0.0964 0.0038 -0.0045 4.0403 0.5826 10.0000 10.0000 9.5330 0.2482 0.0633 0.0994 21.5002 0.0579 0.0259 0.0808 0.0011 -0.0119 4.1586 0.5458 10.0000 10.0000 9.5211 0.2302 0.0490 0.0993 20.9424 0.0542 0.0227 0.0658 -0.0019 -0.0191 4.2769 0.5098 10.0000 10.0000 9.5078 0.2120 0.0353 0.0992 20.4116 0.0506 0.0198 0.0513 -0.0053 -0.0263 4.3952 0.4750 10.0000 10.0000 9.4810 0.1937 0.0223 0.0991 19.9060 0.0471 0.0172 0.0373 -0.0092 -0.0337 4.5134 0.4417 10.0000 10.0000 9.4322 0.1753 0.0100 0.0992 19.4239 0.0438 0.0148 0.0237 -0.0137 -0.0413 4.6317 0.4102 10.0000 10.0000 9.3550 0.1569 -0.0015 0.0993 18.9637 0.0407 0.0128 0.0108 -0.0188 -0.0489 4.7451 0.3819 10.0000 10.0000 9.1003 0.1393 -0.0117 0.0994 18.5417 0.0380 0.0111 -0.0009 -0.0244 -0.0561 4.7753 0.3735 10.0000 10.0000 8.9963 0.1334 -0.0147 0.0995 18.4328 0.0372 0.0106 -0.0043 -0.0267 -0.0583 4.8005 0.3635 10.0000 10.0000 8.9038 0.1256 -0.0181 0.0995 18.3423 0.0362 0.0100 -0.0082 -0.0302 -0.0606 4.8258 0.3504 10.0000 10.0000 8.8064 0.1148 -0.0225 0.0996 18.2527 0.0349 0.0093 -0.0131 -0.0354 -0.0636 4.8510 0.3338 10.0000 10.0000 8.7055 0.1005 -0.0279 0.0996 18.1639 0.0333 0.0085 -0.0191 -0.0426 -0.0673 4.8763 0.3130 10.0000 10.0000 8.6040 0.0820 -0.0346 0.0997 18.0760 0.0312 0.0074 -0.0266 -0.0522 -0.0717 4.9015 0.2865 10.0000 10.0000 8.5005 0.0581 -0.0431 0.0997 17.9889 0.0286 0.0062 -0.0358 -0.0648 -0.0771 4.9268 0.2514 10.0000 10.0000 8.3977 0.0259 -0.0540 0.0998 17.9026 0.0251 0.0048 -0.0478 -0.0820 -0.0841 4.9520 0.1994 10.0000 10.0000 8.3065 -0.0227 -0.0701 0.0998 17.8171 0.0199 0.0030 -0.0653 -0.1083 -0.0941 4.9773 0.1061 10.0000 10.0000 8.3133 -0.1107 -0.0986 0.0999 17.7324 0.0106 0.0009 -0.0961 -0.1564 -0.1115 5.0000 0.0163 10.0000 10.0050 10.0050 -0.1955 -0.1258 0.1000 17.6651 0.0016 0.0000 -0.1258 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.045723 TOTAL WEIGHT (Kg) = 0.020736 TOTAL VOLUME (IN**3) = 0.744887 TOTAL PROJECTED AREA (IN**2) = 6.3952 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000477 MOMENT OF INERTIA (Kg-M**2) = 0.000054 STATIC MOMENT, ONE SIDE (IN-LB) = 0.036302 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 = 91.861 INNER LIMIT (NORMALIZED BY RADIUS) = 0.080 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 15122.32 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.20, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.66, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412