FAUVEL 14% AIRFOIL (fauvel-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FAUVEL 14% AIRFOIL (fauvel-il) Reynolds number: 50,000 Max Cl/Cd: 18.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fauvel-il-50000-n5.txt Download as CSV file: xf-fauvel-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FAUVEL 14% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5369 0.11193 0.10534 0.0083 1.0000 0.0711
-10.500 -0.5345 0.10731 0.10078 0.0062 1.0000 0.0709
-10.250 -0.5356 0.10216 0.09570 0.0033 1.0000 0.0706
-10.000 -0.5401 0.09641 0.09000 -0.0004 1.0000 0.0705
-9.750 -0.5465 0.09036 0.08401 -0.0046 1.0000 0.0701
-9.500 -0.5580 0.08434 0.07802 -0.0086 1.0000 0.0696
-9.250 -0.5738 0.07881 0.07248 -0.0113 1.0000 0.0691
-9.000 -0.5908 0.07403 0.06767 -0.0123 1.0000 0.0687
-8.750 -0.6064 0.06975 0.06332 -0.0121 1.0000 0.0684
-8.500 -0.6163 0.06549 0.05888 -0.0121 0.8869 0.0680
-8.250 -0.6181 0.06119 0.05408 -0.0122 0.8344 0.0677
-8.000 -0.6198 0.05761 0.05005 -0.0107 0.8094 0.0676
-7.750 -0.6183 0.05432 0.04631 -0.0089 0.7915 0.0677
-7.500 -0.6133 0.05133 0.04286 -0.0070 0.7767 0.0682
-7.250 -0.6058 0.04860 0.03960 -0.0051 0.7638 0.0693
-7.000 -0.5955 0.04599 0.03641 -0.0031 0.7515 0.0705
-6.750 -0.5803 0.04372 0.03372 -0.0016 0.7397 0.0716
-6.500 -0.5611 0.04189 0.03166 -0.0005 0.7286 0.0726
-6.250 -0.5401 0.04008 0.02960 0.0005 0.7171 0.0736
-6.000 -0.5183 0.03843 0.02766 0.0015 0.7068 0.0748
-5.750 -0.4952 0.03697 0.02592 0.0024 0.6961 0.0768
-5.500 -0.4706 0.03561 0.02422 0.0031 0.6860 0.0795
-5.250 -0.4446 0.03431 0.02263 0.0038 0.6763 0.0819
-5.000 -0.4167 0.03311 0.02138 0.0039 0.6659 0.0841
-4.750 -0.3878 0.03207 0.02019 0.0042 0.6568 0.0868
-4.500 -0.3565 0.03113 0.01912 0.0040 0.6463 0.0908
-4.250 -0.3257 0.03027 0.01819 0.0040 0.6376 0.0958
-4.000 -0.2939 0.02951 0.01739 0.0036 0.6271 0.1021
-3.750 -0.2640 0.02877 0.01658 0.0037 0.6185 0.1086
-3.500 -0.2368 0.02812 0.01591 0.0040 0.6092 0.1196
-3.250 -0.2129 0.02739 0.01533 0.0048 0.6012 0.1364
-3.000 -0.1915 0.02659 0.01488 0.0059 0.5924 0.1696
-2.750 -0.1732 0.02579 0.01450 0.0074 0.5855 0.2545
-2.500 -0.1595 0.02477 0.01410 0.0095 0.5772 0.3639
-2.250 -0.0952 0.02504 0.01620 0.0091 0.5674 0.8269
-2.000 -0.0151 0.02672 0.01745 0.0041 0.5564 0.9043
-1.750 0.0379 0.02716 0.01762 0.0003 0.5463 0.9316
-1.500 0.0771 0.02721 0.01737 -0.0016 0.5392 0.9453
-1.250 0.1176 0.02731 0.01731 -0.0042 0.5300 0.9578
-1.000 0.1595 0.02722 0.01698 -0.0069 0.5230 0.9692
-0.750 0.2040 0.02720 0.01682 -0.0105 0.5144 0.9813
-0.500 0.2523 0.02693 0.01635 -0.0146 0.5070 0.9946
-0.250 0.2852 0.02691 0.01621 -0.0162 0.5004 1.0000
0.000 0.3067 0.02710 0.01635 -0.0157 0.4938 1.0000
0.250 0.3273 0.02714 0.01626 -0.0147 0.4890 1.0000
0.500 0.3487 0.02741 0.01647 -0.0141 0.4829 1.0000
0.750 0.3699 0.02769 0.01673 -0.0136 0.4766 1.0000
1.000 0.3904 0.02780 0.01672 -0.0125 0.4722 1.0000
1.250 0.4112 0.02807 0.01694 -0.0118 0.4674 1.0000
1.500 0.4322 0.02862 0.01752 -0.0115 0.4607 1.0000
1.750 0.4524 0.02884 0.01767 -0.0105 0.4561 1.0000
2.000 0.4724 0.02892 0.01764 -0.0091 0.4526 1.0000
2.250 0.4922 0.02983 0.01865 -0.0090 0.4458 1.0000
2.500 0.5116 0.03035 0.01917 -0.0082 0.4408 1.0000
2.750 0.5311 0.03060 0.01935 -0.0069 0.4370 1.0000
3.000 0.5503 0.03102 0.01973 -0.0058 0.4330 1.0000
3.250 0.5671 0.03226 0.02111 -0.0056 0.4261 1.0000
3.500 0.5852 0.03283 0.02167 -0.0045 0.4217 1.0000
3.750 0.6042 0.03313 0.02192 -0.0030 0.4185 1.0000
4.000 0.6198 0.03425 0.02311 -0.0023 0.4133 1.0000
4.250 0.6330 0.03565 0.02462 -0.0017 0.4070 1.0000
4.500 0.6498 0.03626 0.02523 -0.0002 0.4030 1.0000
4.750 0.6686 0.03654 0.02546 0.0014 0.4001 1.0000
5.000 0.6737 0.03894 0.02803 0.0019 0.3931 1.0000
5.250 0.6836 0.04037 0.02952 0.0031 0.3876 1.0000
5.500 0.7002 0.04086 0.02999 0.0048 0.3840 1.0000
5.750 0.7208 0.04091 0.03001 0.0066 0.3815 1.0000
6.000 0.6991 0.04580 0.03511 0.0070 0.3713 1.0000
6.250 0.7131 0.04650 0.03582 0.0088 0.3673 1.0000
6.500 0.7352 0.04637 0.03566 0.0107 0.3646 1.0000
7.000 0.7069 0.05349 0.04289 0.0127 0.3490 1.0000
7.250 0.7355 0.05260 0.04198 0.0149 0.3467 1.0000
7.750 0.6969 0.06037 0.04974 0.0165 0.3302 1.0000
8.250 0.6702 0.06684 0.05618 0.0181 0.3144 1.0000
8.750 0.6601 0.07249 0.06181 0.0188 0.2994 1.0000
9.000 0.6896 0.07166 0.06101 0.0207 0.2962 1.0000
9.250 0.6585 0.07765 0.06698 0.0192 0.2848 1.0000
9.500 0.6816 0.07758 0.06694 0.0206 0.2809 1.0000
9.750 0.6610 0.08270 0.07207 0.0193 0.2708 1.0000
10.000 0.6778 0.08344 0.07285 0.0202 0.2661 1.0000
10.500 0.6760 0.08939 0.07885 0.0196 0.2517 1.0000
10.750 0.7023 0.08887 0.07837 0.0211 0.2486 1.0000
11.000 0.6751 0.09562 0.08513 0.0186 0.2380 1.0000
11.250 0.6959 0.09586 0.08540 0.0197 0.2343 1.0000
11.500 0.6764 0.10180 0.09136 0.0174 0.2251 1.0000
11.750 0.6907 0.10300 0.09262 0.0179 0.2206 1.0000
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Polar data table (+)
Polar graphs
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