6x6E (6x6E.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 0.0900 0.0000 0.0000 0.2500 0.0000 0.1343 0.0000 0.0672 0.0000 0.0750 0.0000 0.0000 0.0800 0.4786 0.7653 0.0140 -0.2397 0.2468 0.0095 0.1318 1.5898 0.0631 0.0812 0.0824 0.0065 -0.0169 0.1600 0.4640 1.3997 0.1070 -0.4372 0.2449 0.0349 0.1293 6.0770 0.0600 0.0831 0.1011 0.0133 -0.0074 0.2400 0.4600 1.9931 0.3414 -0.4615 0.2442 0.0719 0.1271 12.7554 0.0584 0.0811 0.1260 0.0196 0.0079 0.3200 0.4695 2.5455 0.7533 -0.2177 0.2446 0.1161 0.1249 20.5393 0.0586 0.0761 0.1561 0.0255 0.0272 0.4000 0.4925 3.0570 1.3476 0.3360 0.2457 0.1635 0.1229 28.2007 0.0605 0.0692 0.1902 0.0307 0.0489 0.4800 0.5254 3.5275 2.0954 1.1827 0.2475 0.2100 0.1210 34.7908 0.0636 0.0612 0.2261 0.0355 0.0714 0.5600 0.5619 3.9571 2.9352 2.2453 0.2496 0.2514 0.1192 39.8350 0.0670 0.0527 0.2601 0.0398 0.0931 0.6400 0.5950 4.3457 3.7773 3.3196 0.2520 0.2835 0.1176 43.2082 0.0700 0.0446 0.2880 0.0436 0.1119 0.7200 0.6180 4.6934 4.5086 4.2597 0.2544 0.3022 0.1161 44.9033 0.0718 0.0374 0.3051 0.0465 0.1253 0.8000 0.6251 5.0001 4.9983 4.9088 0.2565 0.3034 0.1148 44.8385 0.0717 0.0321 0.3059 0.0473 0.1300 0.8794 0.6194 5.2639 5.2639 5.2581 0.2583 0.2915 0.1135 43.6121 0.0703 0.0293 0.2945 0.0460 0.1254 0.9479 0.6134 5.4593 5.4593 5.4644 0.2593 0.2791 0.1124 42.5083 0.0689 0.0287 0.2831 0.0443 0.1172 1.0159 0.6071 5.6232 5.6232 5.6066 0.2598 0.2653 0.1112 41.3797 0.0675 0.0292 0.2706 0.0421 0.1064 1.0838 0.6004 5.7576 5.7576 5.7120 0.2600 0.2498 0.1101 40.2148 0.0661 0.0295 0.2568 0.0397 0.0940 1.1517 0.5932 5.8625 5.8625 5.7861 0.2597 0.2337 0.1090 39.0120 0.0647 0.0296 0.2426 0.0373 0.0819 1.2197 0.5856 5.9379 5.9379 5.8389 0.2590 0.2184 0.1079 37.7700 0.0632 0.0292 0.2285 0.0351 0.0714 1.2876 0.5775 5.9837 5.9837 5.8752 0.2578 0.2040 0.1068 36.4876 0.0617 0.0284 0.2148 0.0333 0.0631 1.3555 0.5690 6.0000 6.0000 5.8912 0.2563 0.1903 0.1057 35.1636 0.0601 0.0273 0.2015 0.0317 0.0565 1.4234 0.5601 6.0000 6.0000 5.8911 0.2544 0.1770 0.1046 33.8559 0.0586 0.0263 0.1884 0.0302 0.0501 1.4914 0.5507 6.0000 6.0000 5.8910 0.2520 0.1640 0.1034 32.6314 0.0570 0.0252 0.1756 0.0288 0.0438 1.5593 0.5410 6.0000 6.0000 5.8909 0.2493 0.1513 0.1023 31.4835 0.0554 0.0241 0.1631 0.0275 0.0375 1.6272 0.5307 6.0000 6.0000 5.8909 0.2462 0.1390 0.1012 30.4061 0.0537 0.0231 0.1509 0.0263 0.0313 1.6952 0.5201 6.0000 6.0000 5.8911 0.2427 0.1269 0.1001 29.3936 0.0521 0.0220 0.1390 0.0252 0.0251 1.7631 0.5090 6.0000 6.0000 5.8913 0.2388 0.1152 0.0990 28.4408 0.0504 0.0209 0.1273 0.0241 0.0189 1.8310 0.4975 6.0000 6.0000 5.8916 0.2346 0.1038 0.0979 27.5432 0.0487 0.0198 0.1159 0.0231 0.0129 1.8990 0.4856 6.0000 6.0000 5.8921 0.2300 0.0927 0.0968 26.6964 0.0470 0.0187 0.1048 0.0221 0.0069 1.9669 0.4732 6.0000 6.0000 5.8930 0.2251 0.0819 0.0956 25.8966 0.0453 0.0176 0.0939 0.0211 0.0010 2.0348 0.4604 6.0000 6.0000 5.8943 0.2198 0.0715 0.0945 25.1403 0.0435 0.0166 0.0834 0.0200 -0.0048 2.1028 0.4471 6.0000 6.0000 5.8959 0.2142 0.0613 0.0934 24.4243 0.0418 0.0155 0.0731 0.0190 -0.0104 2.1707 0.4334 6.0000 6.0000 5.8977 0.2082 0.0515 0.0923 23.7456 0.0400 0.0144 0.0632 0.0179 -0.0160 2.2386 0.4193 6.0000 6.0000 5.8999 0.2020 0.0420 0.0912 23.1017 0.0382 0.0134 0.0535 0.0168 -0.0214 2.3066 0.4048 6.0000 6.0000 5.9027 0.1953 0.0327 0.0901 22.4899 0.0365 0.0124 0.0440 0.0157 -0.0267 2.3745 0.3898 6.0000 6.0000 5.9062 0.1884 0.0238 0.0890 21.9082 0.0347 0.0114 0.0349 0.0145 -0.0318 2.4424 0.3744 6.0000 6.0000 5.9105 0.1812 0.0152 0.0878 21.3544 0.0329 0.0104 0.0260 0.0133 -0.0367 2.5103 0.3586 6.0000 6.0000 5.9150 0.1736 0.0069 0.0867 20.8267 0.0311 0.0095 0.0174 0.0121 -0.0415 2.5783 0.3423 6.0000 6.0000 5.9207 0.1658 -0.0011 0.0856 20.3234 0.0293 0.0086 0.0091 0.0108 -0.0461 2.6462 0.3256 6.0000 6.0000 5.9278 0.1577 -0.0087 0.0845 19.8429 0.0275 0.0077 0.0011 0.0095 -0.0505 2.7141 0.3084 6.0000 6.0000 5.9357 0.1493 -0.0161 0.0834 19.3837 0.0257 0.0069 -0.0067 0.0082 -0.0547 2.7821 0.2909 6.0000 6.0000 5.9456 0.1406 -0.0231 0.0823 18.9445 0.0239 0.0061 -0.0142 0.0068 -0.0587 2.8472 0.2719 6.0000 6.0000 5.9559 0.1303 -0.0302 0.0812 18.5408 0.0221 0.0053 -0.0217 0.0047 -0.0627 2.8652 0.2633 6.0000 6.0000 5.9588 0.1244 -0.0331 0.0809 18.4328 0.0213 0.0049 -0.0248 0.0025 -0.0644 2.8803 0.2542 6.0000 6.0000 5.9615 0.1176 -0.0361 0.0807 18.3423 0.0205 0.0046 -0.0281 -0.0002 -0.0661 2.8955 0.2433 6.0000 6.0000 5.9684 0.1090 -0.0396 0.0804 18.2527 0.0196 0.0042 -0.0320 -0.0039 -0.0683 2.9106 0.2300 6.0000 6.0000 5.9835 0.0983 -0.0438 0.0802 18.1639 0.0184 0.0037 -0.0366 -0.0088 -0.0709 2.9258 0.2139 6.0000 6.0000 6.0046 0.0849 -0.0489 0.0799 18.0760 0.0171 0.0032 -0.0422 -0.0150 -0.0740 2.9409 0.1940 6.0000 6.0000 6.0361 0.0677 -0.0551 0.0797 17.9889 0.0155 0.0027 -0.0490 -0.0232 -0.0778 2.9561 0.1679 6.0000 6.0000 6.0894 0.0448 -0.0631 0.0794 17.9026 0.0133 0.0020 -0.0578 -0.0344 -0.0829 2.9712 0.1278 6.0000 6.0000 6.2158 0.0085 -0.0753 0.0792 17.8171 0.0101 0.0012 -0.0713 -0.0526 -0.0906 2.9864 0.0667 6.0000 6.0000 6.6968 -0.0479 -0.0938 0.0789 17.7324 0.0053 0.0003 -0.0917 -0.0811 -0.1023 3.0000 0.0116 6.0000 6.0030 6.0030 -0.0988 -0.1103 0.0787 17.6652 0.0009 0.0000 -0.1103 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.011220 TOTAL WEIGHT (Kg) = 0.005088 TOTAL VOLUME (IN**3) = 0.182790 TOTAL PROJECTED AREA (IN**2) = 2.4456 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000039 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.005010 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 = 97.062 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 24823.84 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.80, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.30, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412