XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-5 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4694 0.08832 0.08602 -0.0164 0.8513 0.0209 -8.750 -0.4772 0.08124 0.07893 -0.0218 0.8429 0.0211 -8.500 -0.4786 0.07613 0.07379 -0.0268 0.8332 0.0213 -8.250 -0.4768 0.07204 0.06962 -0.0300 0.8251 0.0215 -8.000 -0.4708 0.06824 0.06575 -0.0326 0.8161 0.0217 -7.750 -0.4631 0.06453 0.06195 -0.0350 0.8082 0.0220 -7.500 -0.4530 0.06097 0.05829 -0.0372 0.7997 0.0224 -7.250 -0.4412 0.05720 0.05439 -0.0394 0.7917 0.0232 -7.000 -0.4275 0.05289 0.04987 -0.0415 0.7839 0.0244 -6.750 -0.4065 0.04684 0.04327 -0.0435 0.7767 0.0262 -6.500 -0.3903 0.04252 0.03859 -0.0440 0.7692 0.0263 -6.000 -0.3639 0.02593 0.02081 -0.0441 0.7561 0.0208 -5.750 -0.3416 0.02209 0.01638 -0.0438 0.7493 0.0211 -5.500 -0.3168 0.02051 0.01470 -0.0440 0.7415 0.0221 -5.250 -0.2899 0.02020 0.01434 -0.0442 0.7346 0.0232 -5.000 -0.2631 0.01826 0.01206 -0.0439 0.7273 0.0240 -4.500 -0.2074 0.01626 0.00953 -0.0436 0.7139 0.0262 -4.250 -0.1813 0.01461 0.00778 -0.0435 0.7076 0.0281 -4.000 -0.1532 0.01434 0.00747 -0.0437 0.7008 0.0302 -3.750 -0.1249 0.01395 0.00696 -0.0437 0.6941 0.0323 -3.500 -0.0979 0.01293 0.00583 -0.0435 0.6882 0.0343 -3.250 -0.0700 0.01245 0.00536 -0.0437 0.6819 0.0368 -3.000 -0.0420 0.01218 0.00503 -0.0438 0.6763 0.0394 -2.750 -0.0135 0.01190 0.00469 -0.0439 0.6705 0.0412 -2.500 0.0139 0.01123 0.00398 -0.0439 0.6647 0.0437 -2.250 0.0417 0.01088 0.00356 -0.0440 0.6598 0.0461 -2.000 0.0704 0.01061 0.00329 -0.0442 0.6545 0.0489 -1.750 0.0991 0.01039 0.00303 -0.0444 0.6493 0.0513 -1.500 0.1276 0.01019 0.00274 -0.0446 0.6447 0.0537 -1.250 0.1564 0.00993 0.00250 -0.0448 0.6396 0.0600 -1.000 0.1853 0.00972 0.00233 -0.0451 0.6345 0.0751 -0.750 0.2090 0.00782 0.00209 -0.0457 0.6302 0.5980 -0.500 0.2357 0.00756 0.00215 -0.0454 0.6260 0.7005 -0.250 0.2632 0.00747 0.00219 -0.0452 0.6216 0.7480 0.000 0.2907 0.00745 0.00222 -0.0450 0.6176 0.7846 0.500 0.3449 0.00741 0.00228 -0.0443 0.6092 0.8380 0.750 0.3709 0.00739 0.00233 -0.0437 0.6045 0.8660 1.000 0.3947 0.00741 0.00238 -0.0425 0.6003 0.8968 1.250 0.4196 0.00742 0.00242 -0.0417 0.5961 0.9169 1.500 0.4455 0.00740 0.00243 -0.0411 0.5914 0.9334 1.750 0.4723 0.00740 0.00240 -0.0408 0.5869 0.9493 2.000 0.5027 0.00744 0.00241 -0.0413 0.5829 0.9656 2.250 0.5390 0.00745 0.00244 -0.0432 0.5787 0.9806 2.500 0.5775 0.00749 0.00247 -0.0456 0.5743 0.9969 2.750 0.6074 0.00759 0.00251 -0.0463 0.5704 1.0000 3.000 0.6361 0.00768 0.00260 -0.0467 0.5661 1.0000 3.250 0.6651 0.00775 0.00268 -0.0472 0.5614 1.0000 3.500 0.6939 0.00785 0.00275 -0.0476 0.5570 1.0000 3.750 0.7226 0.00797 0.00285 -0.0479 0.5520 1.0000 4.000 0.7515 0.00804 0.00296 -0.0483 0.5459 1.0000 4.250 0.7800 0.00815 0.00304 -0.0486 0.5404 1.0000 4.500 0.8087 0.00824 0.00316 -0.0490 0.5340 1.0000 4.750 0.8373 0.00832 0.00327 -0.0493 0.5272 1.0000 5.000 0.8657 0.00844 0.00340 -0.0496 0.5208 1.0000 5.250 0.8942 0.00851 0.00350 -0.0499 0.5119 1.0000 5.500 0.9226 0.00859 0.00362 -0.0502 0.5016 1.0000 5.750 0.9507 0.00867 0.00371 -0.0504 0.4876 1.0000 6.000 0.9787 0.00878 0.00383 -0.0507 0.4721 1.0000 6.250 1.0064 0.00892 0.00399 -0.0509 0.4536 1.0000 6.500 1.0332 0.00919 0.00417 -0.0511 0.4231 1.0000 6.750 1.0577 0.00975 0.00451 -0.0510 0.3770 1.0000 7.000 1.0810 0.01049 0.00501 -0.0510 0.3234 1.0000 7.250 1.1024 0.01144 0.00567 -0.0508 0.2703 1.0000 7.500 1.1247 0.01224 0.00630 -0.0506 0.2334 1.0000 7.750 1.1457 0.01314 0.00696 -0.0503 0.1849 1.0000 8.000 1.1609 0.01460 0.00800 -0.0495 0.1194 1.0000 8.250 1.1792 0.01563 0.00887 -0.0489 0.0857 1.0000 8.500 1.1974 0.01659 0.00970 -0.0483 0.0651 1.0000 8.750 1.2158 0.01746 0.01054 -0.0476 0.0516 1.0000 9.000 1.2325 0.01841 0.01144 -0.0468 0.0406 1.0000 9.250 1.2474 0.01945 0.01247 -0.0458 0.0329 1.0000 9.500 1.2566 0.02074 0.01377 -0.0443 0.0285 1.0000 9.750 1.2696 0.02180 0.01490 -0.0433 0.0261 1.0000 10.000 1.2793 0.02317 0.01630 -0.0422 0.0243 1.0000 10.250 1.2820 0.02517 0.01837 -0.0407 0.0228 1.0000 10.500 1.2934 0.02648 0.01978 -0.0399 0.0221 1.0000 10.750 1.3026 0.02802 0.02141 -0.0391 0.0213 1.0000 11.000 1.3112 0.02965 0.02311 -0.0383 0.0205 1.0000 11.250 1.3191 0.03136 0.02489 -0.0376 0.0198 1.0000 11.500 1.3258 0.03322 0.02681 -0.0370 0.0191 1.0000 11.750 1.3280 0.03552 0.02917 -0.0361 0.0185 1.0000 12.000 1.3256 0.03827 0.03200 -0.0351 0.0180 1.0000 12.250 1.3277 0.04059 0.03441 -0.0342 0.0177 1.0000 12.500 1.3340 0.04257 0.03649 -0.0336 0.0174 1.0000 12.750 1.3392 0.04463 0.03865 -0.0329 0.0171 1.0000 13.000 1.3438 0.04678 0.04089 -0.0323 0.0168 1.0000 13.250 1.3480 0.04898 0.04318 -0.0317 0.0165 1.0000 13.500 1.3520 0.05121 0.04550 -0.0311 0.0162 1.0000 13.750 1.3564 0.05349 0.04787 -0.0307 0.0158 1.0000 14.000 1.3604 0.05586 0.05032 -0.0304 0.0154 1.0000 14.250 1.3641 0.05832 0.05286 -0.0303 0.0151 1.0000 14.500 1.3670 0.06086 0.05546 -0.0301 0.0148 1.0000 14.750 1.3690 0.06351 0.05820 -0.0299 0.0145 1.0000 15.000 1.3700 0.06623 0.06100 -0.0294 0.0142 1.0000 15.250 1.3690 0.06909 0.06396 -0.0282 0.0139 1.0000 15.500 1.3668 0.07239 0.06742 -0.0277 0.0137 1.0000 15.750 1.3652 0.07585 0.07104 -0.0282 0.0136 1.0000 16.000 1.3623 0.07956 0.07491 -0.0288 0.0135 1.0000 16.250 1.3580 0.08353 0.07904 -0.0297 0.0134 1.0000 16.500 1.3523 0.08782 0.08349 -0.0307 0.0132 1.0000 16.750 1.3453 0.09244 0.08828 -0.0321 0.0131 1.0000 17.000 1.3370 0.09736 0.09337 -0.0337 0.0129 1.0000 17.250 1.3275 0.10259 0.09876 -0.0356 0.0128 1.0000 17.500 1.3168 0.10820 0.10454 -0.0379 0.0126 1.0000 17.750 1.3053 0.11416 0.11065 -0.0405 0.0125 1.0000 18.000 1.2918 0.12067 0.11734 -0.0436 0.0124 1.0000 18.250 1.2773 0.12760 0.12444 -0.0472 0.0124 1.0000 18.500 1.2612 0.13517 0.13218 -0.0513 0.0123 1.0000 18.750 1.2414 0.14391 0.14112 -0.0564 0.0123 1.0000 19.000 1.2183 0.15402 0.15142 -0.0626 0.0124 1.0000 19.250 1.1884 0.16661 0.16423 -0.0707 0.0126 1.0000