FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 200,000 Max Cl/Cd: 50.07 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l100-il-200000.txt Download as CSV file: xf-fx79l100-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5525 0.10712 0.10373 -0.0035 1.0000 0.0661
-11.500 -0.5376 0.10494 0.10152 -0.0016 1.0000 0.0675
-11.000 -0.6311 0.07157 0.06817 -0.0184 1.0000 0.0439
-10.750 -0.6095 0.07325 0.06988 -0.0155 1.0000 0.0460
-10.500 -0.6069 0.07188 0.06854 -0.0164 1.0000 0.0564
-10.250 -0.8185 0.06431 0.06029 -0.0256 1.0000 0.0409
-10.000 -0.8340 0.05981 0.05571 -0.0250 1.0000 0.0396
-9.750 -0.8514 0.05503 0.05071 -0.0238 1.0000 0.0387
-9.500 -0.8673 0.04925 0.04458 -0.0222 1.0000 0.0369
-9.250 -0.8919 0.04090 0.03530 -0.0188 1.0000 0.0344
-9.000 -0.8861 0.03704 0.03100 -0.0168 1.0000 0.0343
-8.750 -0.8724 0.03467 0.02842 -0.0155 1.0000 0.0353
-8.500 -0.8552 0.03315 0.02678 -0.0145 1.0000 0.0372
-8.250 -0.8396 0.03082 0.02411 -0.0129 1.0000 0.0387
-8.000 -0.8217 0.02898 0.02190 -0.0115 1.0000 0.0405
-7.750 -0.8020 0.02739 0.01997 -0.0101 1.0000 0.0417
-7.500 -0.7830 0.02436 0.01677 -0.0091 1.0000 0.0440
-7.250 -0.7615 0.02337 0.01576 -0.0082 1.0000 0.0474
-7.000 -0.7390 0.02214 0.01438 -0.0073 1.0000 0.0501
-6.750 -0.7158 0.02118 0.01321 -0.0062 1.0000 0.0526
-6.500 -0.6950 0.01941 0.01147 -0.0052 1.0000 0.0569
-6.250 -0.6727 0.01855 0.01059 -0.0042 1.0000 0.0612
-6.000 -0.6498 0.01784 0.00975 -0.0031 1.0000 0.0653
-5.750 -0.6307 0.01657 0.00861 -0.0017 1.0000 0.0720
-5.500 -0.6088 0.01592 0.00786 -0.0006 1.0000 0.0790
-5.250 -0.5898 0.01497 0.00701 0.0009 1.0000 0.0879
-5.000 -0.5699 0.01420 0.00631 0.0023 1.0000 0.1007
-4.750 -0.5502 0.01346 0.00564 0.0038 1.0000 0.1191
-4.500 -0.5328 0.01249 0.00497 0.0054 1.0000 0.1601
-4.250 -0.5208 0.01110 0.00432 0.0078 1.0000 0.2880
-4.000 -0.5092 0.01017 0.00413 0.0105 1.0000 0.4396
-3.750 -0.4921 0.00992 0.00413 0.0127 1.0000 0.5128
-3.500 -0.4744 0.00985 0.00413 0.0147 1.0000 0.5523
-3.250 -0.4593 0.00986 0.00416 0.0170 1.0000 0.5811
-3.000 -0.4201 0.00986 0.00418 0.0145 0.9899 0.6120
-2.750 -0.3766 0.00982 0.00418 0.0113 0.9773 0.6380
-2.500 -0.3337 0.00979 0.00414 0.0083 0.9647 0.6609
-2.250 -0.2905 0.00976 0.00414 0.0054 0.9520 0.6833
-2.000 -0.2486 0.00973 0.00413 0.0028 0.9376 0.7054
-1.750 -0.2081 0.00969 0.00410 0.0006 0.9220 0.7236
-1.500 -0.1706 0.00965 0.00405 -0.0011 0.9051 0.7392
-1.250 -0.1370 0.00962 0.00398 -0.0019 0.8877 0.7522
-1.000 -0.1072 0.00962 0.00392 -0.0020 0.8708 0.7647
-0.750 -0.0793 0.00961 0.00389 -0.0017 0.8546 0.7761
-0.500 -0.0523 0.00960 0.00386 -0.0012 0.8396 0.7872
-0.250 -0.0259 0.00960 0.00384 -0.0007 0.8255 0.7991
0.000 0.0000 0.00960 0.00383 0.0000 0.8119 0.8120
0.250 0.0258 0.00960 0.00384 0.0007 0.7992 0.8256
0.500 0.0522 0.00960 0.00386 0.0012 0.7872 0.8395
0.750 0.0793 0.00961 0.00389 0.0017 0.7759 0.8544
1.000 0.1071 0.00962 0.00392 0.0020 0.7649 0.8707
1.250 0.1370 0.00962 0.00399 0.0019 0.7523 0.8877
1.500 0.1705 0.00965 0.00405 0.0011 0.7392 0.9051
1.750 0.2081 0.00969 0.00410 -0.0006 0.7238 0.9221
2.000 0.2485 0.00973 0.00412 -0.0028 0.7052 0.9376
2.250 0.2903 0.00975 0.00414 -0.0054 0.6833 0.9519
2.500 0.3336 0.00979 0.00415 -0.0084 0.6614 0.9646
2.750 0.3764 0.00982 0.00417 -0.0113 0.6369 0.9773
3.000 0.4202 0.00986 0.00418 -0.0145 0.6122 0.9900
3.250 0.4594 0.00986 0.00418 -0.0171 0.5817 1.0000
3.500 0.4744 0.00985 0.00413 -0.0147 0.5524 1.0000
3.750 0.4919 0.00992 0.00412 -0.0127 0.5109 1.0000
4.000 0.5092 0.01017 0.00413 -0.0106 0.4400 1.0000
4.250 0.5209 0.01109 0.00432 -0.0078 0.2893 1.0000
4.500 0.5327 0.01250 0.00496 -0.0055 0.1590 1.0000
4.750 0.5501 0.01345 0.00563 -0.0038 0.1199 1.0000
5.000 0.5699 0.01420 0.00630 -0.0023 0.1008 1.0000
5.250 0.5897 0.01497 0.00702 -0.0009 0.0882 1.0000
5.500 0.6089 0.01590 0.00785 0.0005 0.0791 1.0000
5.750 0.6307 0.01658 0.00862 0.0017 0.0725 1.0000
6.000 0.6503 0.01771 0.00964 0.0030 0.0658 1.0000
6.250 0.6727 0.01857 0.01060 0.0042 0.0617 1.0000
6.500 0.6950 0.01940 0.01147 0.0052 0.0571 1.0000
6.750 0.7158 0.02124 0.01326 0.0062 0.0528 1.0000
7.000 0.7389 0.02207 0.01431 0.0072 0.0497 1.0000
7.250 0.7612 0.02302 0.01537 0.0082 0.0464 1.0000
7.500 0.7826 0.02429 0.01663 0.0090 0.0433 1.0000
7.750 0.8020 0.02708 0.01969 0.0101 0.0413 1.0000
8.000 0.8215 0.02886 0.02181 0.0115 0.0400 1.0000
8.250 0.8393 0.03085 0.02417 0.0130 0.0382 1.0000
8.500 0.8549 0.03318 0.02682 0.0145 0.0369 1.0000
8.750 0.8729 0.03456 0.02827 0.0154 0.0351 1.0000
9.000 0.8850 0.03735 0.03135 0.0169 0.0344 1.0000
9.250 0.8939 0.04046 0.03476 0.0185 0.0340 1.0000
9.500 0.8681 0.04906 0.04436 0.0222 0.0365 1.0000
9.750 0.8501 0.05522 0.05091 0.0238 0.0387 1.0000
10.000 0.8350 0.05990 0.05578 0.0249 0.0399 1.0000
10.250 0.8180 0.06437 0.06035 0.0255 0.0408 1.0000
10.750 0.6163 0.07108 0.06770 0.0169 0.0455 1.0000
11.000 0.6423 0.06910 0.06566 0.0205 0.0437 1.0000
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Polar data table (+)
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