9x6SF (9x6SF.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 1.0600 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0300 0.0000 0.0000 0.0750 0.4770 1.4236 0.0090 -0.3037 0.2498 0.0046 0.0967 1.0929 0.0461 0.0771 0.0338 0.0084 -0.0569 0.1500 0.4551 1.7732 0.0706 -0.5904 0.2558 0.0174 0.0927 4.2866 0.0422 0.0772 0.0445 0.0262 -0.0523 0.2250 0.4378 2.1090 0.2330 -0.8106 0.2672 0.0367 0.0889 9.3595 0.0389 0.0783 0.0602 0.0487 -0.0453 0.3000 0.4293 2.4308 0.5354 -0.8276 0.2829 0.0608 0.0852 15.8561 0.0366 0.0746 0.0771 0.0745 -0.0361 0.3750 0.4325 2.7388 0.9984 -0.5351 0.3018 0.0879 0.0817 22.9648 0.0353 0.0670 0.0976 0.1019 -0.0249 0.4500 0.4481 3.0329 1.6123 0.1004 0.3230 0.1165 0.0783 29.6933 0.0351 0.0578 0.1222 0.1292 -0.0121 0.5250 0.4743 3.3131 2.3268 1.0240 0.3454 0.1449 0.0751 35.1979 0.0356 0.0485 0.1486 0.1549 0.0021 0.6000 0.5076 3.5794 3.0510 2.0814 0.3681 0.1716 0.0721 38.9836 0.0366 0.0405 0.1743 0.1776 0.0176 0.6750 0.5445 3.8318 3.6691 3.0311 0.3901 0.1949 0.0692 40.8636 0.0377 0.0350 0.1973 0.1952 0.0333 0.7500 0.5823 4.0703 4.0689 3.6016 0.4104 0.2133 0.0665 40.8086 0.0387 0.0336 0.2157 0.2047 0.0470 0.8273 0.6204 4.3016 4.3016 3.8841 0.4295 0.2278 0.0639 39.6091 0.0396 0.0356 0.2304 0.2069 0.0576 0.9440 0.6751 4.6227 4.6227 4.2834 0.4563 0.2466 0.0602 37.9329 0.0406 0.0379 0.2497 0.2090 0.0718 1.0629 0.7272 4.9155 4.9155 4.6558 0.4813 0.2622 0.0569 36.3536 0.0413 0.0395 0.2657 0.2099 0.0844 1.1819 0.7754 5.1734 5.1734 4.9867 0.5041 0.2744 0.0539 34.8632 0.0418 0.0403 0.2784 0.2095 0.0951 1.3009 0.8199 5.3963 5.3963 5.2716 0.5245 0.2833 0.0514 33.4336 0.0421 0.0405 0.2877 0.2079 0.1039 1.4198 0.8604 5.5843 5.5843 5.5103 0.5425 0.2891 0.0492 32.0453 0.0424 0.0401 0.2941 0.2052 0.1110 1.5388 0.8969 5.7373 5.7373 5.7020 0.5583 0.2920 0.0475 30.6849 0.0426 0.0395 0.2975 0.2015 0.1165 1.6578 0.9295 5.8553 5.8553 5.8494 0.5717 0.2921 0.0461 29.3425 0.0429 0.0386 0.2982 0.1971 0.1205 1.7767 0.9580 5.9384 5.9384 5.9559 0.5828 0.2897 0.0452 28.0108 0.0433 0.0377 0.2963 0.1921 0.1231 1.8957 0.9823 5.9866 5.9866 6.0220 0.5916 0.2847 0.0447 26.6845 0.0439 0.0369 0.2920 0.1868 0.1244 2.0147 1.0025 6.0000 6.0000 6.0448 0.5980 0.2774 0.0445 25.3606 0.0446 0.0363 0.2856 0.1813 0.1246 2.1336 1.0184 6.0000 6.0000 6.0509 0.6021 0.2680 0.0445 24.1115 0.0453 0.0358 0.2771 0.1759 0.1230 2.2526 1.0299 6.0000 6.0000 6.0551 0.6039 0.2568 0.0445 22.9733 0.0458 0.0355 0.2667 0.1704 0.1195 2.3716 1.0371 6.0000 6.0000 6.0574 0.6033 0.2439 0.0445 21.9327 0.0462 0.0353 0.2547 0.1649 0.1141 2.4905 1.0399 6.0000 6.0000 6.0578 0.6005 0.2296 0.0445 20.9781 0.0463 0.0352 0.2412 0.1593 0.1071 2.6095 1.0382 6.0000 6.0000 6.0575 0.5953 0.2140 0.0445 20.0999 0.0462 0.0350 0.2263 0.1533 0.0986 2.7284 1.0320 6.0000 6.0000 6.0576 0.5877 0.1974 0.0445 19.2895 0.0459 0.0346 0.2103 0.1471 0.0889 2.8474 1.0211 6.0000 6.0000 6.0582 0.5779 0.1798 0.0445 18.5398 0.0454 0.0339 0.1932 0.1406 0.0782 2.9664 1.0056 6.0000 6.0000 6.0594 0.5657 0.1615 0.0445 17.8443 0.0447 0.0329 0.1754 0.1337 0.0666 3.0853 0.9854 6.0000 6.0000 6.0612 0.5512 0.1427 0.0445 17.1976 0.0438 0.0316 0.1569 0.1266 0.0544 3.2043 0.9604 6.0000 6.0000 6.0637 0.5343 0.1234 0.0445 16.5948 0.0427 0.0301 0.1380 0.1191 0.0416 3.3233 0.9305 6.0000 6.0000 6.0671 0.5152 0.1040 0.0445 16.0318 0.0414 0.0283 0.1188 0.1114 0.0285 3.4422 0.8957 6.0000 6.0000 6.0717 0.4937 0.0846 0.0445 15.5048 0.0399 0.0263 0.0994 0.1035 0.0152 3.5612 0.8560 6.0000 6.0000 6.0777 0.4699 0.0654 0.0445 15.0106 0.0381 0.0241 0.0801 0.0953 0.0020 3.6802 0.8113 6.0000 6.0000 6.0856 0.4437 0.0466 0.0445 14.5463 0.0361 0.0218 0.0611 0.0868 -0.0110 3.7991 0.7615 6.0000 6.0000 6.0953 0.4152 0.0284 0.0445 14.1092 0.0339 0.0193 0.0424 0.0782 -0.0236 3.9181 0.7066 6.0000 6.0000 6.1079 0.3844 0.0109 0.0445 13.6972 0.0314 0.0168 0.0244 0.0695 -0.0356 4.0371 0.6464 6.0000 6.0000 6.1252 0.3513 -0.0057 0.0445 13.3082 0.0288 0.0142 0.0071 0.0606 -0.0469 4.1560 0.5811 6.0000 6.0000 6.1476 0.3159 -0.0212 0.0445 12.9402 0.0259 0.0116 -0.0093 0.0516 -0.0571 4.2700 0.5086 6.0000 6.0000 6.1781 0.2750 -0.0358 0.0445 12.6061 0.0226 0.0091 -0.0252 0.0405 -0.0667 4.2977 0.4846 6.0000 6.0000 6.1870 0.2592 -0.0404 0.0445 12.5273 0.0216 0.0083 -0.0302 0.0349 -0.0697 4.3205 0.4620 6.0000 6.0000 6.1949 0.2436 -0.0446 0.0445 12.4634 0.0206 0.0076 -0.0349 0.0290 -0.0725 4.3432 0.4364 6.0000 6.0000 6.2036 0.2250 -0.0494 0.0445 12.4002 0.0194 0.0068 -0.0401 0.0217 -0.0757 4.3659 0.4070 6.0000 6.0000 6.2141 0.2030 -0.0549 0.0445 12.3377 0.0181 0.0060 -0.0462 0.0126 -0.0793 4.3886 0.3728 6.0000 6.0000 6.2436 0.1762 -0.0613 0.0445 12.2757 0.0166 0.0050 -0.0533 0.0007 -0.0838 4.4114 0.3316 6.0000 6.0000 6.2867 0.1428 -0.0690 0.0445 12.2144 0.0148 0.0040 -0.0618 -0.0148 -0.0892 4.4341 0.2784 6.0000 6.0000 6.3619 0.0978 -0.0791 0.0445 12.1536 0.0124 0.0029 -0.0730 -0.0363 -0.0963 4.4568 0.1968 6.0000 6.0000 6.5581 0.0250 -0.0949 0.0445 12.0935 0.0088 0.0015 -0.0906 -0.0724 -0.1077 4.4795 0.1028 6.0000 6.0000 7.1718 -0.0598 -0.1131 0.0445 12.0339 0.0046 0.0004 -0.1108 -0.1143 -0.1207 4.5000 0.0181 6.0000 6.0030 6.0030 -0.1361 -0.1293 0.0445 11.9867 0.0008 0.0000 -0.1293 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) = 0.019372 TOTAL WEIGHT (Kg) = 0.008785 TOTAL VOLUME (IN**3) = 0.315589 TOTAL PROJECTED AREA (IN**2) = 6.4171 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000221 MOMENT OF INERTIA (Kg-M**2) = 0.000025 STATIC MOMENT, ONE SIDE (IN-LB) = 0.016656 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 = 129.925 INNER LIMIT (NORMALIZED BY RADIUS) = 0.056 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5887.40 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.00, E63 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.