9x4.1SF (9x41SF.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 0.5000 -0.0248 0.0000 0.0000 0.2500 0.0000 0.1170 0.0000 0.0585 0.0000 0.0500 0.0000 0.0000 0.0750 0.4931 0.3488 0.0081 -0.0813 0.2471 0.0048 0.1107 0.9906 0.0546 0.0420 0.0535 0.0008 0.0028 0.1500 0.4885 0.6998 0.0613 -0.1412 0.2460 0.0180 0.1048 3.7233 0.0512 0.0461 0.0624 0.0027 0.0046 0.2250 0.4882 1.0289 0.1930 -0.1091 0.2468 0.0372 0.0992 7.7730 0.0484 0.0470 0.0739 0.0060 0.0085 0.3000 0.4942 1.3368 0.4218 0.0652 0.2494 0.0607 0.0940 12.6127 0.0465 0.0453 0.0882 0.0105 0.0142 0.3750 0.5073 1.6242 0.7497 0.4021 0.2539 0.0864 0.0892 17.6502 0.0452 0.0417 0.1057 0.0162 0.0213 0.4500 0.5271 1.8919 1.1609 0.8847 0.2603 0.1123 0.0847 22.3227 0.0446 0.0370 0.1253 0.0229 0.0295 0.5250 0.5519 2.1405 1.6223 1.4360 0.2686 0.1366 0.0805 26.1876 0.0444 0.0319 0.1453 0.0307 0.0385 0.6000 0.5791 2.3707 2.0856 1.9924 0.2789 0.1572 0.0767 28.9521 0.0444 0.0270 0.1634 0.0395 0.0478 0.6750 0.6058 2.5832 2.4921 2.4717 0.2910 0.1722 0.0731 30.4381 0.0443 0.0231 0.1770 0.0485 0.0563 0.7500 0.6299 2.7788 2.7779 2.7930 0.3051 0.1796 0.0699 30.5192 0.0440 0.0211 0.1841 0.0557 0.0618 0.8273 0.6520 2.9633 2.9633 2.9923 0.3203 0.1816 0.0668 29.6865 0.0436 0.0206 0.1864 0.0600 0.0642 0.9440 0.6845 3.2107 3.2107 3.2511 0.3408 0.1834 0.0628 28.4282 0.0430 0.0206 0.1887 0.0644 0.0668 1.0629 0.7162 3.4269 3.4269 3.4686 0.3588 0.1840 0.0593 27.1634 0.0425 0.0213 0.1899 0.0668 0.0684 1.1819 0.7430 3.6095 3.6095 3.6515 0.3738 0.1834 0.0564 25.9227 0.0419 0.0220 0.1899 0.0682 0.0699 1.3009 0.7645 3.7613 3.7613 3.8035 0.3860 0.1817 0.0540 24.7109 0.0413 0.0224 0.1889 0.0690 0.0714 1.4198 0.7810 3.8850 3.8850 3.9277 0.3956 0.1790 0.0521 23.5325 0.0407 0.0227 0.1868 0.0693 0.0728 1.5388 0.7929 3.9834 3.9834 4.0266 0.4025 0.1752 0.0507 22.3916 0.0402 0.0229 0.1837 0.0690 0.0739 1.6578 0.8003 4.0594 4.0594 4.1032 0.4069 0.1705 0.0497 21.2921 0.0397 0.0229 0.1797 0.0682 0.0747 1.7767 0.8036 4.1156 4.1156 4.1603 0.4089 0.1650 0.0490 20.2374 0.0394 0.0228 0.1748 0.0670 0.0750 1.8957 0.8031 4.1550 4.1550 4.2006 0.4086 0.1587 0.0486 19.2308 0.0390 0.0226 0.1692 0.0654 0.0746 2.0147 0.7990 4.1803 4.1803 4.2270 0.4061 0.1516 0.0485 18.2750 0.0387 0.0224 0.1627 0.0633 0.0737 2.1336 0.7916 4.1942 4.1942 4.2423 0.4015 0.1438 0.0485 17.3729 0.0384 0.0220 0.1556 0.0606 0.0719 2.2526 0.7813 4.1996 4.1996 4.2494 0.3949 0.1354 0.0484 16.5267 0.0379 0.0214 0.1479 0.0572 0.0694 2.3716 0.7682 4.2000 4.2000 4.2520 0.3864 0.1265 0.0484 15.7411 0.0372 0.0207 0.1396 0.0531 0.0661 2.4905 0.7527 4.2000 4.2000 4.2546 0.3760 0.1172 0.0484 15.0240 0.0364 0.0199 0.1307 0.0484 0.0619 2.6095 0.7350 4.2000 4.2000 4.2577 0.3640 0.1075 0.0484 14.3681 0.0356 0.0190 0.1214 0.0429 0.0570 2.7284 0.7155 4.2000 4.2000 4.2614 0.3503 0.0974 0.0484 13.7659 0.0346 0.0181 0.1117 0.0366 0.0514 2.8474 0.6944 4.2000 4.2000 4.2657 0.3351 0.0871 0.0483 13.2114 0.0336 0.0170 0.1017 0.0296 0.0453 2.9664 0.6720 4.2000 4.2000 4.2707 0.3185 0.0766 0.0483 12.6990 0.0325 0.0160 0.0914 0.0217 0.0386 3.0853 0.6485 4.2000 4.2000 4.2764 0.3005 0.0660 0.0483 12.2244 0.0313 0.0150 0.0808 0.0130 0.0315 3.2043 0.6244 4.2000 4.2000 4.2830 0.2813 0.0553 0.0483 11.7835 0.0301 0.0139 0.0701 0.0034 0.0239 3.3233 0.5997 4.2000 4.2000 4.2904 0.2610 0.0445 0.0482 11.3728 0.0289 0.0129 0.0592 -0.0070 0.0161 3.4422 0.5749 4.2000 4.2000 4.2983 0.2397 0.0337 0.0482 10.9895 0.0277 0.0119 0.0483 -0.0184 0.0080 3.5612 0.5503 4.2000 4.2000 4.3070 0.2174 0.0230 0.0482 10.6309 0.0265 0.0110 0.0374 -0.0307 -0.0003 3.6802 0.5260 4.2000 4.2000 4.3167 0.1943 0.0123 0.0482 10.2947 0.0253 0.0101 0.0266 -0.0440 -0.0087 3.7991 0.5024 4.1987 4.1987 4.3262 0.1705 0.0019 0.0481 9.9759 0.0242 0.0092 0.0158 -0.0582 -0.0171 3.9181 0.4797 4.1849 4.1849 4.3239 0.1460 -0.0085 0.0481 9.6477 0.0231 0.0085 0.0053 -0.0734 -0.0255 4.0371 0.4583 4.1561 4.1561 4.3065 0.1210 -0.0186 0.0481 9.3050 0.0220 0.0078 -0.0051 -0.0897 -0.0338 4.1560 0.4384 4.1121 4.1121 4.2745 0.0956 -0.0285 0.0481 8.9490 0.0211 0.0072 -0.0151 -0.1070 -0.0419 4.2700 0.4015 4.0558 4.0558 4.2299 0.0516 -0.0406 0.0480 8.5964 0.0193 0.0060 -0.0279 -0.1348 -0.0519 4.2977 0.3865 4.0400 4.0400 4.2187 0.0346 -0.0444 0.0480 8.5090 0.0186 0.0056 -0.0321 -0.1450 -0.0550 4.3205 0.3720 4.0265 4.0265 4.2168 0.0183 -0.0478 0.0480 8.4369 0.0179 0.0052 -0.0359 -0.1549 -0.0579 4.3432 0.3551 4.0124 4.0124 4.2174 -0.0003 -0.0515 0.0480 8.3644 0.0171 0.0048 -0.0401 -0.1661 -0.0610 4.3659 0.3354 3.9977 3.9977 4.2219 -0.0218 -0.0556 0.0480 8.2915 0.0161 0.0043 -0.0448 -0.1790 -0.0645 4.3886 0.3123 3.9825 3.9825 4.2322 -0.0469 -0.0602 0.0480 8.2182 0.0150 0.0037 -0.0500 -0.1938 -0.0684 4.4114 0.2846 3.9667 3.9667 4.2472 -0.0765 -0.0653 0.0480 8.1445 0.0137 0.0031 -0.0560 -0.2116 -0.0729 4.4341 0.2503 3.9504 3.9504 4.2500 -0.1127 -0.0714 0.0480 8.0704 0.0120 0.0026 -0.0631 -0.2351 -0.0791 4.4568 0.2052 3.9336 3.9336 4.2778 -0.1598 -0.0787 0.0480 7.9960 0.0099 0.0019 -0.0719 -0.2640 -0.0863 4.4795 0.1330 3.9162 3.9162 4.5218 -0.2339 -0.0894 0.0480 7.9212 0.0064 0.0008 -0.0851 -0.3052 -0.0954 4.5000 0.0196 3.9000 3.9038 3.9038 -0.3485 -0.1057 0.0480 7.8611 0.0009 0.0000 -0.1057 0.0000 0.0000 RADIUS: 4.51 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.010960 TOTAL WEIGHT (Kg) = 0.004971 TOTAL VOLUME (IN**3) = 0.178556 TOTAL PROJECTED AREA (IN**2) = 5.3706 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000117 MOMENT OF INERTIA (Kg-M**2) = 0.000013 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009050 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 = 93.160 INNER LIMIT (NORMALIZED BY RADIUS) = 0.055 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4396.62 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.40, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.50, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412