FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il) Reynolds number: 100,000 Max Cl/Cd: 39.46 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71l150-il-100000.txt Download as CSV file: xf-fx71l150-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/30 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7146 0.11124 0.10582 -0.0114 1.0000 0.0666
-13.250 -0.7308 0.10269 0.09726 -0.0157 1.0000 0.0651
-13.000 -0.8949 0.07778 0.07165 -0.0336 1.0000 0.0598
-12.750 -0.8996 0.07350 0.06729 -0.0344 1.0000 0.0593
-12.500 -0.9151 0.06902 0.06266 -0.0353 1.0000 0.0588
-12.250 -0.9321 0.06482 0.05828 -0.0356 1.0000 0.0583
-12.000 -0.9501 0.06096 0.05420 -0.0352 1.0000 0.0579
-11.750 -0.9651 0.05750 0.05051 -0.0341 1.0000 0.0573
-11.500 -0.9771 0.05437 0.04712 -0.0322 1.0000 0.0569
-11.250 -0.9848 0.05147 0.04396 -0.0299 1.0000 0.0566
-11.000 -0.9856 0.04859 0.04078 -0.0280 1.0000 0.0565
-10.750 -0.9806 0.04604 0.03795 -0.0265 1.0000 0.0570
-10.500 -0.9721 0.04365 0.03529 -0.0251 1.0000 0.0577
-10.250 -0.9611 0.04141 0.03275 -0.0238 1.0000 0.0587
-10.000 -0.9464 0.03925 0.03027 -0.0226 1.0000 0.0595
-9.750 -0.9230 0.03698 0.02788 -0.0225 1.0000 0.0608
-9.500 -0.8954 0.03507 0.02599 -0.0227 1.0000 0.0623
-9.250 -0.8682 0.03332 0.02421 -0.0227 1.0000 0.0643
-9.000 -0.8418 0.03170 0.02242 -0.0224 1.0000 0.0669
-8.750 -0.8135 0.03008 0.02102 -0.0227 1.0000 0.0706
-8.500 -0.7902 0.02866 0.01962 -0.0221 1.0000 0.0759
-8.250 -0.7724 0.02729 0.01835 -0.0210 1.0000 0.0841
-8.000 -0.7619 0.02569 0.01704 -0.0194 1.0000 0.0957
-7.750 -0.7549 0.02431 0.01589 -0.0174 1.0000 0.1125
-7.500 -0.7540 0.02311 0.01493 -0.0145 1.0000 0.1333
-7.250 -0.7694 0.02262 0.01456 -0.0089 1.0000 0.1467
-7.000 -0.7646 0.02129 0.01360 -0.0073 0.9925 0.1862
-6.750 -0.7421 0.01929 0.01229 -0.0092 0.9798 0.2838
-6.500 -0.7172 0.01818 0.01186 -0.0102 0.9690 0.3912
-6.250 -0.6831 0.01818 0.01212 -0.0115 0.9604 0.4658
-6.000 -0.6440 0.01878 0.01272 -0.0131 0.9527 0.5167
-5.750 -0.6065 0.01981 0.01376 -0.0136 0.9446 0.5480
-5.500 -0.5661 0.02103 0.01492 -0.0143 0.9373 0.5717
-5.250 -0.5268 0.02215 0.01598 -0.0148 0.9304 0.5889
-5.000 -0.4934 0.02302 0.01677 -0.0145 0.9222 0.6039
-4.750 -0.4570 0.02365 0.01725 -0.0151 0.9159 0.6189
-4.500 -0.4251 0.02460 0.01817 -0.0142 0.9078 0.6293
-4.250 -0.3913 0.02527 0.01877 -0.0139 0.9010 0.6406
-4.000 -0.3646 0.02557 0.01896 -0.0132 0.8941 0.6532
-3.750 -0.3425 0.02567 0.01897 -0.0123 0.8864 0.6660
-3.500 -0.3071 0.02616 0.01942 -0.0121 0.8813 0.6729
-3.250 -0.2860 0.02617 0.01937 -0.0111 0.8743 0.6834
-3.000 -0.2656 0.02603 0.01913 -0.0101 0.8672 0.6946
-2.750 -0.2362 0.02623 0.01929 -0.0095 0.8610 0.7018
-2.500 -0.2164 0.02608 0.01909 -0.0083 0.8528 0.7110
-2.250 -0.1961 0.02582 0.01873 -0.0072 0.8464 0.7212
-2.000 -0.1728 0.02585 0.01875 -0.0063 0.8387 0.7288
-1.750 -0.1489 0.02573 0.01858 -0.0055 0.8332 0.7369
-1.500 -0.1325 0.02555 0.01836 -0.0046 0.8266 0.7466
-1.250 -0.1055 0.02562 0.01842 -0.0040 0.8209 0.7523
-1.000 -0.0861 0.02541 0.01816 -0.0032 0.8157 0.7610
-0.750 -0.0638 0.02549 0.01826 -0.0025 0.8085 0.7671
-0.500 -0.0428 0.02525 0.01797 -0.0017 0.8029 0.7751
-0.250 -0.0215 0.02537 0.01811 -0.0008 0.7949 0.7811
0.000 0.0000 0.02519 0.01789 0.0000 0.7891 0.7890
0.250 0.0215 0.02537 0.01812 0.0009 0.7812 0.7950
0.500 0.0428 0.02525 0.01797 0.0017 0.7751 0.8030
0.750 0.0638 0.02548 0.01826 0.0025 0.7670 0.8085
1.000 0.0861 0.02540 0.01815 0.0032 0.7610 0.8157
1.250 0.1055 0.02561 0.01842 0.0040 0.7523 0.8209
1.500 0.1324 0.02555 0.01836 0.0046 0.7466 0.8266
1.750 0.1488 0.02573 0.01858 0.0055 0.7369 0.8332
2.000 0.1727 0.02585 0.01875 0.0063 0.7288 0.8387
2.250 0.1962 0.02582 0.01873 0.0072 0.7212 0.8463
2.500 0.2164 0.02608 0.01908 0.0083 0.7110 0.8528
2.750 0.2362 0.02622 0.01928 0.0095 0.7017 0.8611
3.000 0.2657 0.02603 0.01913 0.0101 0.6946 0.8672
3.250 0.2859 0.02618 0.01937 0.0110 0.6834 0.8743
3.500 0.3072 0.02615 0.01941 0.0121 0.6729 0.8813
3.750 0.3425 0.02567 0.01897 0.0123 0.6660 0.8865
4.000 0.3646 0.02558 0.01897 0.0132 0.6532 0.8941
4.250 0.3912 0.02527 0.01877 0.0139 0.6406 0.9009
4.500 0.4252 0.02461 0.01818 0.0142 0.6294 0.9078
4.750 0.4571 0.02364 0.01725 0.0151 0.6189 0.9160
5.000 0.4935 0.02302 0.01676 0.0145 0.6039 0.9222
5.250 0.5268 0.02216 0.01599 0.0148 0.5890 0.9304
5.500 0.5662 0.02102 0.01491 0.0143 0.5716 0.9373
5.750 0.6065 0.01983 0.01378 0.0136 0.5482 0.9446
6.000 0.6443 0.01878 0.01271 0.0130 0.5176 0.9527
6.250 0.6831 0.01818 0.01212 0.0114 0.4661 0.9605
6.500 0.7173 0.01818 0.01186 0.0101 0.3914 0.9690
6.750 0.7421 0.01928 0.01229 0.0092 0.2837 0.9799
7.000 0.7647 0.02130 0.01360 0.0073 0.1851 0.9926
7.250 0.7690 0.02261 0.01456 0.0089 0.1465 1.0000
7.500 0.7540 0.02311 0.01492 0.0145 0.1333 1.0000
7.750 0.7551 0.02431 0.01589 0.0173 0.1125 1.0000
8.000 0.7623 0.02568 0.01703 0.0193 0.0959 1.0000
8.250 0.7726 0.02729 0.01834 0.0210 0.0840 1.0000
8.500 0.7905 0.02867 0.01962 0.0220 0.0759 1.0000
8.750 0.8136 0.03009 0.02103 0.0226 0.0704 1.0000
9.000 0.8420 0.03170 0.02243 0.0224 0.0668 1.0000
9.250 0.8683 0.03331 0.02419 0.0227 0.0644 1.0000
9.500 0.8957 0.03506 0.02599 0.0226 0.0623 1.0000
9.750 0.9231 0.03698 0.02789 0.0224 0.0609 1.0000
10.000 0.9479 0.03929 0.03028 0.0224 0.0597 1.0000
10.250 0.9611 0.04141 0.03275 0.0237 0.0587 1.0000
10.500 0.9725 0.04368 0.03533 0.0250 0.0578 1.0000
10.750 0.9813 0.04607 0.03799 0.0264 0.0572 1.0000
11.000 0.9860 0.04863 0.04082 0.0280 0.0566 1.0000
11.250 0.9855 0.05149 0.04398 0.0298 0.0568 1.0000
11.500 0.9779 0.05438 0.04714 0.0321 0.0570 1.0000
11.750 0.9657 0.05754 0.05054 0.0340 0.0573 1.0000
12.000 0.9517 0.06093 0.05417 0.0351 0.0579 1.0000
12.250 0.9329 0.06484 0.05830 0.0355 0.0583 1.0000
12.500 0.9173 0.06896 0.06260 0.0352 0.0588 1.0000
12.750 0.9005 0.07349 0.06729 0.0343 0.0593 1.0000
13.000 0.8926 0.07797 0.07186 0.0334 0.0598 1.0000
13.250 0.6911 0.11318 0.10781 0.0085 0.0688 1.0000
13.500 0.7096 0.11305 0.10766 0.0100 0.0678 1.0000
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