FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il) Reynolds number: 100,000 Max Cl/Cd: 38.74 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711525-il-100000.txt Download as CSV file: xf-fx711525-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7440 0.10229 0.09686 -0.0172 1.0000 0.0669
-13.000 -0.7533 0.09585 0.09041 -0.0202 1.0000 0.0655
-12.750 -0.8147 0.08310 0.07744 -0.0286 1.0000 0.0633
-12.500 -0.9324 0.07133 0.06495 -0.0347 1.0000 0.0608
-12.250 -0.9277 0.06759 0.06117 -0.0349 1.0000 0.0602
-12.000 -0.9370 0.06380 0.05723 -0.0348 1.0000 0.0597
-11.750 -0.9488 0.06025 0.05350 -0.0341 1.0000 0.0591
-11.500 -0.9625 0.05687 0.04989 -0.0326 1.0000 0.0585
-11.250 -0.9743 0.05380 0.04656 -0.0303 1.0000 0.0579
-11.000 -0.9788 0.05066 0.04310 -0.0283 1.0000 0.0574
-10.750 -0.9773 0.04758 0.03968 -0.0267 1.0000 0.0569
-10.500 -0.9700 0.04475 0.03652 -0.0253 1.0000 0.0567
-10.250 -0.9568 0.04215 0.03365 -0.0243 1.0000 0.0568
-10.000 -0.9386 0.03983 0.03110 -0.0236 1.0000 0.0571
-9.750 -0.9171 0.03767 0.02875 -0.0232 1.0000 0.0578
-9.500 -0.8930 0.03566 0.02657 -0.0230 1.0000 0.0589
-9.250 -0.8671 0.03381 0.02453 -0.0229 1.0000 0.0603
-9.000 -0.8372 0.03204 0.02284 -0.0233 1.0000 0.0624
-8.750 -0.8123 0.03071 0.02153 -0.0232 1.0000 0.0658
-8.500 -0.7878 0.02934 0.02026 -0.0230 1.0000 0.0698
-8.250 -0.7665 0.02804 0.01901 -0.0224 1.0000 0.0757
-8.000 -0.7496 0.02669 0.01780 -0.0213 1.0000 0.0837
-7.750 -0.7407 0.02528 0.01663 -0.0195 1.0000 0.0946
-7.500 -0.7418 0.02419 0.01572 -0.0162 1.0000 0.1086
-7.250 -0.7569 0.02362 0.01525 -0.0104 1.0000 0.1187
-7.000 -0.7664 0.02279 0.01453 -0.0057 0.9991 0.1374
-6.750 -0.7453 0.02059 0.01301 -0.0074 0.9866 0.2085
-6.500 -0.7252 0.01872 0.01193 -0.0086 0.9757 0.3236
-6.250 -0.6936 0.01806 0.01185 -0.0102 0.9677 0.4339
-6.000 -0.6607 0.01830 0.01221 -0.0111 0.9588 0.4969
-5.750 -0.6178 0.01917 0.01308 -0.0129 0.9532 0.5432
-5.500 -0.5869 0.02002 0.01389 -0.0126 0.9447 0.5719
-5.250 -0.5420 0.02150 0.01538 -0.0135 0.9395 0.5933
-5.000 -0.5057 0.02256 0.01636 -0.0136 0.9324 0.6100
-4.750 -0.4714 0.02328 0.01697 -0.0139 0.9248 0.6262
-4.500 -0.4226 0.02477 0.01842 -0.0147 0.9204 0.6349
-4.250 -0.3986 0.02518 0.01874 -0.0136 0.9119 0.6484
-4.000 -0.3597 0.02608 0.01958 -0.0137 0.9057 0.6576
-3.750 -0.3298 0.02641 0.01981 -0.0133 0.8990 0.6692
-3.500 -0.3044 0.02674 0.02008 -0.0123 0.8908 0.6793
-3.250 -0.2766 0.02676 0.02001 -0.0120 0.8843 0.6885
-3.000 -0.2506 0.02703 0.02022 -0.0112 0.8771 0.6976
-2.750 -0.2304 0.02694 0.02007 -0.0101 0.8690 0.7076
-2.500 -0.2007 0.02703 0.02010 -0.0097 0.8633 0.7150
-2.250 -0.1883 0.02678 0.01979 -0.0082 0.8547 0.7251
-2.000 -0.1596 0.02690 0.01988 -0.0077 0.8482 0.7317
-1.750 -0.1433 0.02670 0.01961 -0.0064 0.8419 0.7424
-1.500 -0.1189 0.02682 0.01973 -0.0057 0.8342 0.7485
-1.250 -0.1039 0.02652 0.01935 -0.0045 0.8276 0.7585
-1.000 -0.0781 0.02663 0.01946 -0.0039 0.8218 0.7639
-0.750 -0.0668 0.02646 0.01926 -0.0026 0.8138 0.7739
-0.500 -0.0374 0.02645 0.01924 -0.0021 0.8084 0.7788
-0.250 -0.0236 0.02649 0.01928 -0.0008 0.8005 0.7879
0.000 0.0000 0.02648 0.01928 0.0000 0.7940 0.7940
0.250 0.0236 0.02649 0.01928 0.0008 0.7879 0.8005
0.500 0.0374 0.02645 0.01925 0.0021 0.7788 0.8085
0.750 0.0668 0.02646 0.01926 0.0026 0.7739 0.8137
1.000 0.0781 0.02663 0.01947 0.0039 0.7639 0.8218
1.250 0.1038 0.02652 0.01935 0.0045 0.7585 0.8276
1.500 0.1189 0.02682 0.01973 0.0057 0.7485 0.8342
1.750 0.1434 0.02669 0.01960 0.0064 0.7424 0.8419
2.000 0.1595 0.02690 0.01988 0.0077 0.7317 0.8482
2.250 0.1883 0.02678 0.01979 0.0082 0.7251 0.8547
2.500 0.2008 0.02703 0.02010 0.0097 0.7150 0.8633
2.750 0.2304 0.02693 0.02007 0.0101 0.7076 0.8690
3.000 0.2506 0.02702 0.02022 0.0112 0.6976 0.8771
3.250 0.2766 0.02675 0.02001 0.0120 0.6885 0.8842
3.500 0.3045 0.02674 0.02007 0.0123 0.6794 0.8908
3.750 0.3298 0.02640 0.01980 0.0133 0.6692 0.8990
4.000 0.3597 0.02609 0.01959 0.0136 0.6577 0.9057
4.250 0.3986 0.02519 0.01875 0.0136 0.6484 0.9119
4.500 0.4227 0.02475 0.01840 0.0147 0.6349 0.9204
4.750 0.4713 0.02328 0.01696 0.0139 0.6262 0.9248
5.000 0.5057 0.02256 0.01635 0.0136 0.6100 0.9324
5.250 0.5420 0.02151 0.01539 0.0135 0.5933 0.9395
5.500 0.5869 0.02002 0.01389 0.0126 0.5719 0.9448
5.750 0.6177 0.01916 0.01308 0.0129 0.5432 0.9533
6.000 0.6608 0.01829 0.01219 0.0111 0.4965 0.9588
6.250 0.6936 0.01806 0.01185 0.0102 0.4336 0.9678
6.500 0.7252 0.01872 0.01193 0.0086 0.3231 0.9758
6.750 0.7454 0.02059 0.01300 0.0074 0.2082 0.9867
7.000 0.7665 0.02279 0.01454 0.0057 0.1369 0.9992
7.250 0.7563 0.02363 0.01526 0.0105 0.1178 1.0000
7.500 0.7418 0.02418 0.01572 0.0162 0.1084 1.0000
7.750 0.7409 0.02528 0.01662 0.0194 0.0947 1.0000
8.000 0.7494 0.02673 0.01782 0.0213 0.0834 1.0000
8.250 0.7668 0.02805 0.01901 0.0224 0.0758 1.0000
8.500 0.7883 0.02934 0.02026 0.0229 0.0700 1.0000
8.750 0.8126 0.03072 0.02153 0.0231 0.0657 1.0000
9.000 0.8380 0.03207 0.02287 0.0232 0.0625 1.0000
9.250 0.8678 0.03381 0.02452 0.0228 0.0603 1.0000
9.500 0.8933 0.03566 0.02658 0.0230 0.0589 1.0000
9.750 0.9173 0.03767 0.02876 0.0232 0.0578 1.0000
10.000 0.9389 0.03984 0.03111 0.0236 0.0572 1.0000
10.250 0.9570 0.04219 0.03368 0.0242 0.0568 1.0000
10.500 0.9702 0.04475 0.03653 0.0252 0.0568 1.0000
10.750 0.9776 0.04760 0.03970 0.0266 0.0569 1.0000
11.000 0.9792 0.05064 0.04309 0.0283 0.0574 1.0000
11.250 0.9745 0.05383 0.04659 0.0302 0.0580 1.0000
11.500 0.9631 0.05690 0.04993 0.0325 0.0586 1.0000
11.750 0.9495 0.06026 0.05351 0.0340 0.0591 1.0000
12.000 0.9385 0.06379 0.05722 0.0347 0.0597 1.0000
12.250 0.9276 0.06768 0.06126 0.0348 0.0602 1.0000
12.500 0.9333 0.07140 0.06503 0.0346 0.0608 1.0000
12.750 0.8144 0.08326 0.07760 0.0283 0.0633 1.0000
13.000 0.7547 0.09581 0.09037 0.0202 0.0656 1.0000
13.250 0.7447 0.10242 0.09700 0.0171 0.0670 1.0000
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