9x4.4SFR (9x44SFR.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 0.1752 0.0000 0.0000 0.2500 0.0000 0.0903 0.0000 0.0452 0.0000 0.0470 0.0000 0.0000 0.0750 0.4907 0.5488 0.0114 -0.0863 0.2454 0.0060 0.0873 1.3883 0.0428 0.0426 0.0517 0.0001 0.0001 0.1500 0.4929 0.8998 0.0844 -0.1466 0.2459 0.0220 0.0844 5.1185 0.0416 0.0499 0.0626 0.0005 0.0001 0.2250 0.5078 1.2289 0.2570 -0.1082 0.2506 0.0455 0.0817 10.3029 0.0415 0.0539 0.0745 0.0010 0.0000 0.3000 0.5354 1.5368 0.5396 0.0681 0.2586 0.0737 0.0793 15.9760 0.0424 0.0547 0.0909 0.0017 -0.0001 0.3750 0.5738 1.8242 0.9192 0.3829 0.2689 0.1043 0.0770 21.3122 0.0442 0.0529 0.1133 0.0026 -0.0003 0.4500 0.6192 2.0919 1.3661 0.8080 0.2808 0.1346 0.0749 25.7886 0.0464 0.0491 0.1392 0.0035 -0.0003 0.5250 0.6664 2.3405 1.8414 1.2965 0.2932 0.1622 0.0729 29.1713 0.0486 0.0439 0.1649 0.0043 -0.0001 0.6000 0.7099 2.5707 2.3010 1.7904 0.3053 0.1846 0.0711 31.3978 0.0505 0.0383 0.1865 0.0050 0.0002 0.6750 0.7443 2.7832 2.6973 2.2237 0.3162 0.1992 0.0695 32.4555 0.0517 0.0335 0.2008 0.0050 0.0004 0.7500 0.7647 2.9788 2.9780 2.5222 0.3250 0.2036 0.0680 32.2906 0.0520 0.0311 0.2051 0.0038 0.0001 0.8273 0.7747 3.1633 3.1633 2.7012 0.3321 0.2006 0.0667 31.3227 0.0516 0.0307 0.2021 0.0016 -0.0005 0.9440 0.7874 3.4107 3.4107 2.9275 0.3417 0.1954 0.0648 29.9012 0.0510 0.0306 0.1971 -0.0006 -0.0010 1.0629 0.7973 3.6269 3.6269 3.1109 0.3501 0.1893 0.0633 28.5050 0.0505 0.0308 0.1910 -0.0015 -0.0013 1.1819 0.8045 3.8095 3.8095 3.2614 0.3572 0.1831 0.0620 27.1576 0.0499 0.0309 0.1849 -0.0023 -0.0010 1.3009 0.8093 3.9613 3.9613 3.3815 0.3630 0.1759 0.0610 25.8570 0.0494 0.0309 0.1778 -0.0029 -0.0011 1.4198 0.8118 4.0850 4.0850 3.4735 0.3676 0.1681 0.0602 24.6033 0.0489 0.0308 0.1701 -0.0034 -0.0014 1.5388 0.8120 4.1834 4.1834 3.5398 0.3711 0.1591 0.0596 23.3974 0.0484 0.0306 0.1612 -0.0037 -0.0027 1.6578 0.8101 4.2594 4.2594 3.5829 0.3734 0.1507 0.0592 22.2409 0.0479 0.0303 0.1529 -0.0037 -0.0032 1.7767 0.8061 4.3156 4.3156 3.6055 0.3746 0.1425 0.0589 21.1358 0.0475 0.0298 0.1448 -0.0036 -0.0034 1.8957 0.8002 4.3550 4.3550 3.6103 0.3746 0.1346 0.0587 20.0839 0.0470 0.0293 0.1369 -0.0034 -0.0034 2.0147 0.7924 4.3803 4.3803 3.6002 0.3735 0.1269 0.0586 19.0874 0.0464 0.0287 0.1294 -0.0031 -0.0031 2.1336 0.7827 4.3942 4.3942 3.5782 0.3712 0.1195 0.0585 18.1481 0.0458 0.0280 0.1220 -0.0029 -0.0028 2.2526 0.7713 4.3996 4.3996 3.5472 0.3678 0.1124 0.0585 17.2679 0.0451 0.0272 0.1150 -0.0026 -0.0025 2.3716 0.7583 4.4000 4.4000 3.5111 0.3634 0.1055 0.0585 16.4510 0.0443 0.0263 0.1081 -0.0023 -0.0022 2.4905 0.7437 4.4000 4.4000 3.4744 0.3580 0.0989 0.0584 15.7049 0.0435 0.0252 0.1016 -0.0020 -0.0021 2.6095 0.7276 4.4000 4.4000 3.4376 0.3517 0.0926 0.0584 15.0220 0.0425 0.0242 0.0952 -0.0016 -0.0021 2.7284 0.7101 4.4000 4.4000 3.4007 0.3445 0.0865 0.0584 14.3948 0.0415 0.0230 0.0892 -0.0013 -0.0021 2.8474 0.6913 4.4000 4.4000 3.3637 0.3365 0.0806 0.0584 13.8169 0.0403 0.0218 0.0833 -0.0010 -0.0022 2.9664 0.6713 4.4000 4.4000 3.3268 0.3277 0.0751 0.0583 13.2828 0.0392 0.0205 0.0777 -0.0008 -0.0023 3.0853 0.6501 4.4000 4.4000 3.2899 0.3181 0.0697 0.0583 12.7878 0.0379 0.0193 0.0724 -0.0006 -0.0025 3.2043 0.6278 4.4000 4.4000 3.2532 0.3079 0.0646 0.0583 12.3278 0.0366 0.0180 0.0672 -0.0005 -0.0026 3.3233 0.6046 4.4000 4.4000 3.2167 0.2970 0.0598 0.0583 11.8993 0.0352 0.0166 0.0623 -0.0004 -0.0028 3.4422 0.5804 4.4000 4.4000 3.1808 0.2856 0.0552 0.0582 11.4992 0.0338 0.0153 0.0577 -0.0004 -0.0029 3.5612 0.5555 4.4000 4.4000 3.1445 0.2736 0.0508 0.0582 11.1248 0.0323 0.0140 0.0533 -0.0005 -0.0030 3.6802 0.5297 4.4000 4.4000 3.1097 0.2611 0.0467 0.0582 10.7737 0.0308 0.0128 0.0491 -0.0006 -0.0030 3.7991 0.5034 4.3987 4.3987 3.0727 0.2482 0.0428 0.0582 10.4409 0.0293 0.0115 0.0451 -0.0008 -0.0030 3.9181 0.4764 4.3849 4.3849 3.0255 0.2349 0.0391 0.0581 10.0995 0.0277 0.0103 0.0413 -0.0011 -0.0028 4.0371 0.4490 4.3561 4.3561 2.9636 0.2213 0.0357 0.0581 9.7444 0.0261 0.0092 0.0378 -0.0014 -0.0025 4.1560 0.4211 4.3121 4.3121 2.8877 0.2073 0.0324 0.0581 9.3767 0.0245 0.0081 0.0345 -0.0018 -0.0021 4.2700 0.3942 4.2558 4.2558 2.8018 0.1938 0.0295 0.0581 9.0135 0.0229 0.0071 0.0316 -0.0022 -0.0015 4.2977 0.3876 4.2400 4.2400 2.7788 0.1904 0.0288 0.0580 8.9236 0.0225 0.0068 0.0309 -0.0023 -0.0014 4.3205 0.3821 4.2265 4.2265 2.7593 0.1877 0.0283 0.0580 8.8495 0.0222 0.0066 0.0303 -0.0024 -0.0013 4.3432 0.3767 4.2124 4.2124 2.7372 0.1849 0.0277 0.0580 8.7750 0.0219 0.0064 0.0298 -0.0024 -0.0011 4.3659 0.3688 4.1977 4.1979 2.7131 0.1810 0.0270 0.0580 8.7005 0.0214 0.0062 0.0290 -0.0024 -0.0010 4.3886 0.3566 4.1825 4.1833 2.6872 0.1749 0.0260 0.0580 8.6265 0.0207 0.0058 0.0280 -0.0023 -0.0008 4.4114 0.3387 4.1667 4.1687 2.6593 0.1660 0.0246 0.0580 8.5532 0.0197 0.0052 0.0265 -0.0022 -0.0007 4.4341 0.3127 4.1504 4.1545 2.6301 0.1530 0.0226 0.0580 8.4815 0.0181 0.0044 0.0243 -0.0020 -0.0005 4.4568 0.2738 4.1336 4.1418 2.5995 0.1337 0.0197 0.0580 8.4133 0.0159 0.0034 0.0212 -0.0018 -0.0003 4.4795 0.2092 4.1162 4.1348 2.5732 0.1017 0.0150 0.0580 8.3574 0.0121 0.0020 0.0162 -0.0017 -0.0001 4.5000 0.0514 4.1000 4.1867 4.1867 0.0233 0.0037 0.0580 8.4228 0.0030 0.0000 0.0036 0.0000 0.0000 RADIUS: 4.50 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) = 0.014124 TOTAL WEIGHT (Kg) = 0.006406 TOTAL VOLUME (IN**3) = 0.230102 TOTAL PROJECTED AREA (IN**2) = 5.5283 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000150 MOMENT OF INERTIA (Kg-M**2) = 0.000017 STATIC MOMENT, ONE SIDE (IN-LB) = 0.011720 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 = 92.038 INNER LIMIT (NORMALIZED BY RADIUS) = 0.056 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5638.44 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.50, APC16006R (Transition Start, Airfoil 1) AIRFOIL2: 4.00, APC16006R (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.