FX 75-VG-166/22 (fx75vg166-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 75-VG-166/22 (fx75vg166-il) Reynolds number: 500,000 Max Cl/Cd: 82.42 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx75vg166-il-500000.txt Download as CSV file: xf-fx75vg166-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 75-VG-166/22
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1716 0.08906 0.08580 -0.1005 0.7617 0.0296
-12.500 -0.4913 0.05007 0.04575 -0.1260 0.7650 0.0173
-12.250 -0.5042 0.04711 0.04268 -0.1246 0.7643 0.0171
-12.000 -0.5291 0.04346 0.03878 -0.1216 0.7635 0.0171
-11.750 -0.5343 0.04130 0.03652 -0.1195 0.7626 0.0166
-11.500 -0.5515 0.03840 0.03334 -0.1157 0.7616 0.0169
-11.250 -0.5654 0.03542 0.03006 -0.1116 0.7606 0.0169
-11.000 -0.5659 0.03323 0.02765 -0.1087 0.7596 0.0165
-10.750 -0.5677 0.03151 0.02565 -0.1052 0.7588 0.0171
-10.500 -0.5608 0.02963 0.02353 -0.1028 0.7580 0.0172
-10.250 -0.5486 0.02814 0.02183 -0.1010 0.7573 0.0172
-10.000 -0.5404 0.02732 0.02079 -0.0983 0.7566 0.0176
-9.750 -0.5147 0.02547 0.01875 -0.0986 0.7559 0.0181
-9.500 -0.4928 0.02457 0.01782 -0.0981 0.7552 0.0186
-9.250 -0.4738 0.02390 0.01713 -0.0971 0.7544 0.0191
-9.000 -0.4569 0.02340 0.01660 -0.0958 0.7535 0.0201
-8.750 -0.4351 0.02270 0.01582 -0.0951 0.7526 0.0209
-8.500 -0.4130 0.02208 0.01511 -0.0943 0.7516 0.0215
-8.250 -0.3875 0.02117 0.01415 -0.0942 0.7506 0.0222
-8.000 -0.3685 0.02059 0.01360 -0.0931 0.7494 0.0233
-7.750 -0.3496 0.02011 0.01311 -0.0919 0.7481 0.0244
-7.500 -0.3308 0.01970 0.01266 -0.0906 0.7469 0.0256
-7.250 -0.3119 0.01935 0.01225 -0.0893 0.7458 0.0264
-7.000 -0.2972 0.01869 0.01163 -0.0875 0.7448 0.0284
-6.750 -0.2805 0.01830 0.01122 -0.0858 0.7439 0.0295
-6.500 -0.2623 0.01808 0.01096 -0.0844 0.7430 0.0316
-6.250 -0.2505 0.01760 0.01046 -0.0819 0.7421 0.0332
-6.000 -0.2362 0.01737 0.01024 -0.0798 0.7412 0.0356
-5.750 -0.2222 0.01731 0.01015 -0.0775 0.7403 0.0379
-5.500 -0.2133 0.01702 0.00989 -0.0744 0.7388 0.0410
-5.250 -0.2008 0.01682 0.00973 -0.0719 0.7368 0.0449
-5.000 -0.1861 0.01656 0.00951 -0.0698 0.7348 0.0519
-4.750 -0.1707 0.01629 0.00931 -0.0678 0.7332 0.0649
-4.500 -0.1572 0.01589 0.00910 -0.0655 0.7316 0.1020
-4.250 -0.1471 0.01528 0.00885 -0.0628 0.7302 0.1826
-4.000 -0.1397 0.01449 0.00856 -0.0597 0.7288 0.2996
-3.750 -0.1338 0.01358 0.00820 -0.0563 0.7277 0.4339
-3.500 -0.1321 0.01250 0.00785 -0.0519 0.7265 0.6072
-3.250 -0.1105 0.01302 0.00885 -0.0497 0.7257 0.7171
-3.000 -0.0815 0.01373 0.00953 -0.0495 0.7249 0.7400
-2.750 -0.0574 0.01431 0.01010 -0.0488 0.7222 0.7553
-2.500 -0.0330 0.01480 0.01055 -0.0483 0.7198 0.7674
-2.250 -0.0040 0.01555 0.01130 -0.0479 0.7180 0.7726
-2.000 0.0229 0.01604 0.01175 -0.0474 0.7164 0.7819
-1.750 0.0535 0.01691 0.01264 -0.0468 0.7153 0.7862
-1.500 0.0802 0.01740 0.01309 -0.0463 0.7142 0.7961
-1.250 0.1105 0.01798 0.01367 -0.0456 0.7134 0.7988
-1.000 0.1397 0.01826 0.01392 -0.0454 0.7126 0.8015
-0.750 0.1671 0.01834 0.01397 -0.0453 0.7118 0.8051
-0.500 0.1915 0.01825 0.01381 -0.0452 0.7109 0.8116
-0.250 0.2202 0.01825 0.01379 -0.0451 0.7101 0.8129
0.000 0.2360 0.01857 0.01418 -0.0430 0.7052 0.8150
0.250 0.2593 0.01869 0.01431 -0.0422 0.7028 0.8174
0.500 0.2840 0.01869 0.01430 -0.0419 0.7011 0.8207
0.750 0.3095 0.01855 0.01411 -0.0424 0.6997 0.8260
1.000 0.3363 0.01837 0.01392 -0.0421 0.6987 0.8271
1.250 0.3641 0.01822 0.01376 -0.0420 0.6977 0.8283
1.500 0.3927 0.01803 0.01356 -0.0422 0.6968 0.8296
1.750 0.4224 0.01780 0.01332 -0.0426 0.6960 0.8311
2.000 0.4520 0.01761 0.01310 -0.0430 0.6952 0.8327
2.250 0.4625 0.01797 0.01356 -0.0406 0.6892 0.8355
2.500 0.4895 0.01781 0.01340 -0.0409 0.6871 0.8376
2.750 0.5201 0.01762 0.01319 -0.0421 0.6855 0.8405
3.000 0.5488 0.01715 0.01273 -0.0421 0.6841 0.8417
3.250 0.5794 0.01675 0.01234 -0.0425 0.6830 0.8427
3.500 0.6101 0.01641 0.01200 -0.0431 0.6821 0.8435
3.750 0.6413 0.01610 0.01169 -0.0439 0.6812 0.8442
4.000 0.6606 0.01611 0.01177 -0.0426 0.6770 0.8454
4.250 0.6874 0.01575 0.01145 -0.0426 0.6729 0.8464
4.500 0.7267 0.01474 0.01041 -0.0445 0.6697 0.8469
4.750 0.7634 0.01401 0.00966 -0.0461 0.6672 0.8476
5.000 0.7873 0.01384 0.00955 -0.0456 0.6629 0.8487
5.250 0.8117 0.01365 0.00943 -0.0452 0.6580 0.8502
5.500 0.8425 0.01326 0.00906 -0.0460 0.6543 0.8513
5.750 0.8705 0.01296 0.00878 -0.0462 0.6493 0.8521
6.000 0.8941 0.01279 0.00869 -0.0457 0.6418 0.8530
6.250 0.9212 0.01252 0.00844 -0.0458 0.6335 0.8538
6.500 0.9469 0.01226 0.00818 -0.0456 0.6207 0.8546
6.750 0.9674 0.01209 0.00797 -0.0443 0.5994 0.8555
7.000 0.9819 0.01196 0.00778 -0.0417 0.5747 0.8567
7.250 0.9915 0.01203 0.00775 -0.0383 0.5447 0.8578
7.500 0.9923 0.01230 0.00790 -0.0332 0.5127 0.8592
8.000 0.9612 0.01344 0.00874 -0.0177 0.4482 0.8623
8.250 0.9481 0.01441 0.00961 -0.0115 0.4225 0.8637
8.500 0.9322 0.01598 0.01106 -0.0061 0.3941 0.8652
8.750 0.9168 0.01751 0.01241 -0.0006 0.3600 0.8669
9.000 0.9096 0.01881 0.01356 0.0035 0.3314 0.8678
9.250 0.9040 0.02013 0.01471 0.0073 0.2993 0.8686
9.500 0.8990 0.02150 0.01589 0.0108 0.2628 0.8691
9.750 0.8985 0.02277 0.01699 0.0135 0.2313 0.8696
10.000 0.8997 0.02404 0.01807 0.0160 0.1993 0.8699
10.250 0.9049 0.02517 0.01908 0.0178 0.1756 0.8702
10.500 0.9125 0.02623 0.02003 0.0193 0.1540 0.8704
10.750 0.9221 0.02725 0.02097 0.0204 0.1350 0.8707
11.000 0.9314 0.02841 0.02202 0.0214 0.1143 0.8710
11.250 0.9420 0.02954 0.02306 0.0222 0.0951 0.8713
11.500 0.9505 0.03086 0.02424 0.0231 0.0727 0.8715
11.750 0.9579 0.03232 0.02558 0.0240 0.0546 0.8717
12.000 0.9670 0.03372 0.02692 0.0247 0.0437 0.8719
12.250 0.9767 0.03514 0.02832 0.0253 0.0373 0.8721
12.500 0.9893 0.03641 0.02962 0.0255 0.0343 0.8723
12.750 0.9989 0.03794 0.03116 0.0259 0.0310 0.8724
13.000 1.0115 0.03926 0.03254 0.0261 0.0290 0.8726
13.250 1.0218 0.04083 0.03412 0.0262 0.0269 0.8730
13.500 1.0307 0.04252 0.03588 0.0264 0.0253 0.8732
13.750 1.0416 0.04412 0.03755 0.0265 0.0242 0.8735
14.000 1.0525 0.04572 0.03921 0.0264 0.0231 0.8736
14.250 1.0603 0.04764 0.04118 0.0265 0.0225 0.8736
14.500 1.0607 0.05021 0.04378 0.0269 0.0213 0.8736
14.750 1.0711 0.05198 0.04564 0.0267 0.0206 0.8736
15.000 1.0807 0.05383 0.04758 0.0265 0.0198 0.8737
15.250 1.0884 0.05585 0.04967 0.0264 0.0197 0.8737
15.500 1.0958 0.05800 0.05188 0.0261 0.0188 0.8737
15.750 1.1041 0.06006 0.05399 0.0257 0.0183 0.8737
16.000 1.1072 0.06258 0.05655 0.0256 0.0176 0.8737
16.250 1.1126 0.06481 0.05884 0.0255 0.0174 0.8739
16.500 1.1186 0.06723 0.06138 0.0251 0.0167 0.8741
16.750 1.1258 0.06938 0.06361 0.0249 0.0167 0.8744
17.000 1.1324 0.07181 0.06616 0.0243 0.0163 0.8748
17.250 1.1375 0.07439 0.06884 0.0237 0.0158 0.8750
17.500 1.1434 0.07683 0.07138 0.0231 0.0157 0.8751
17.750 1.1473 0.07955 0.07419 0.0225 0.0153 0.8750
18.000 1.1513 0.08238 0.07712 0.0216 0.0151 0.8750
18.250 1.1547 0.08524 0.08006 0.0208 0.0148 0.8749
18.500 1.1576 0.08817 0.08308 0.0200 0.0147 0.8749
18.750 1.1603 0.09118 0.08614 0.0189 0.0144 0.8749
19.000 1.1619 0.09421 0.08928 0.0181 0.0143 0.8748
19.250 1.1631 0.09708 0.09221 0.0177 0.0139 0.8748
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