FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 50,000 Max Cl/Cd: 36.82 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w097-il-50000-n5.txt Download as CSV file: xf-fx84w097-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-097
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3428 0.10662 0.10011 -0.0236 1.0000 0.0724
-9.750 -0.3386 0.10250 0.09602 -0.0245 1.0000 0.0696
-9.500 -0.4360 0.10508 0.09818 -0.0243 1.0000 0.0610
-9.250 -0.4267 0.10127 0.09438 -0.0244 1.0000 0.0592
-9.000 -0.4233 0.09738 0.09054 -0.0261 1.0000 0.0582
-8.750 -0.4221 0.09338 0.08662 -0.0284 1.0000 0.0579
-8.500 -0.4217 0.08939 0.08271 -0.0307 1.0000 0.0576
-8.250 -0.4232 0.08531 0.07872 -0.0333 1.0000 0.0576
-8.000 -0.4265 0.08119 0.07469 -0.0362 1.0000 0.0573
-7.750 -0.4286 0.07678 0.07035 -0.0395 1.0000 0.0568
-7.500 -0.4304 0.07225 0.06586 -0.0425 1.0000 0.0564
-7.250 -0.4326 0.06786 0.06147 -0.0447 1.0000 0.0559
-7.000 -0.4360 0.06375 0.05732 -0.0457 1.0000 0.0554
-6.750 -0.4411 0.06004 0.05354 -0.0455 1.0000 0.0549
-6.500 -0.4465 0.05662 0.05000 -0.0444 1.0000 0.0544
-6.250 -0.4503 0.05328 0.04646 -0.0431 1.0000 0.0542
-6.000 -0.4507 0.05000 0.04293 -0.0417 1.0000 0.0541
-5.750 -0.4474 0.04681 0.03944 -0.0405 1.0000 0.0544
-5.500 -0.4193 0.04248 0.03454 -0.0437 0.9907 0.0561
-5.250 -0.3875 0.03848 0.02972 -0.0467 0.9818 0.0600
-5.000 -0.3552 0.03502 0.02553 -0.0489 0.9733 0.0624
-4.750 -0.3229 0.03265 0.02288 -0.0507 0.9653 0.0652
-4.500 -0.2869 0.03077 0.02057 -0.0529 0.9581 0.0721
-4.250 -0.2539 0.02891 0.01835 -0.0541 0.9500 0.0777
-4.000 -0.2159 0.02742 0.01655 -0.0561 0.9437 0.0859
-3.750 -0.1835 0.02627 0.01529 -0.0572 0.9353 0.0968
-3.500 -0.1453 0.02511 0.01398 -0.0590 0.9293 0.1105
-3.250 -0.1139 0.02426 0.01298 -0.0597 0.9205 0.1299
-3.000 -0.0780 0.02336 0.01210 -0.0614 0.9138 0.1609
-2.750 -0.0504 0.02255 0.01147 -0.0617 0.9043 0.2044
-2.500 -0.0226 0.02155 0.01095 -0.0622 0.8959 0.2927
-2.250 -0.0017 0.02015 0.01074 -0.0609 0.8877 0.5191
-2.000 0.0340 0.01948 0.01096 -0.0591 0.8821 0.8616
-1.750 0.1357 0.01911 0.01006 -0.0722 0.8823 1.0000
-1.500 0.1616 0.01920 0.00987 -0.0722 0.8722 1.0000
-1.250 0.1827 0.01937 0.00980 -0.0713 0.8608 1.0000
-1.000 0.2049 0.01956 0.00976 -0.0706 0.8503 1.0000
-0.750 0.2308 0.01969 0.00966 -0.0703 0.8417 1.0000
-0.500 0.2511 0.01993 0.00973 -0.0691 0.8308 1.0000
-0.250 0.2724 0.02017 0.00981 -0.0681 0.8207 1.0000
0.000 0.2987 0.02032 0.00980 -0.0677 0.8128 1.0000
0.250 0.3194 0.02061 0.00997 -0.0667 0.8021 1.0000
0.500 0.3420 0.02088 0.01013 -0.0658 0.7925 1.0000
0.750 0.3682 0.02104 0.01019 -0.0653 0.7846 1.0000
1.000 0.3892 0.02138 0.01046 -0.0643 0.7740 1.0000
1.250 0.4131 0.02164 0.01065 -0.0636 0.7651 1.0000
1.500 0.4380 0.02187 0.01082 -0.0630 0.7566 1.0000
1.750 0.4600 0.02223 0.01115 -0.0621 0.7464 1.0000
2.000 0.4860 0.02243 0.01133 -0.0615 0.7386 1.0000
2.250 0.5088 0.02277 0.01167 -0.0608 0.7287 1.0000
2.500 0.5317 0.02313 0.01204 -0.0600 0.7191 1.0000
2.750 0.5589 0.02328 0.01222 -0.0595 0.7117 1.0000
3.000 0.5803 0.02373 0.01272 -0.0586 0.7008 1.0000
3.250 0.6040 0.02408 0.01311 -0.0579 0.6912 1.0000
3.500 0.6307 0.02424 0.01331 -0.0573 0.6831 1.0000
3.750 0.6525 0.02469 0.01388 -0.0565 0.6719 1.0000
4.000 0.6760 0.02505 0.01433 -0.0557 0.6617 1.0000
4.250 0.7038 0.02513 0.01448 -0.0550 0.6535 1.0000
4.500 0.7255 0.02560 0.01507 -0.0542 0.6417 1.0000
4.750 0.7481 0.02600 0.01565 -0.0533 0.6304 1.0000
5.000 0.7725 0.02628 0.01606 -0.0525 0.6195 1.0000
5.250 0.7997 0.02631 0.01622 -0.0516 0.6093 1.0000
5.500 0.8232 0.02657 0.01665 -0.0506 0.5965 1.0000
5.750 0.8462 0.02686 0.01715 -0.0495 0.5831 1.0000
6.000 0.8696 0.02708 0.01757 -0.0484 0.5692 1.0000
6.250 0.8936 0.02721 0.01789 -0.0472 0.5545 1.0000
6.500 0.9188 0.02708 0.01794 -0.0458 0.5378 1.0000
6.750 0.9383 0.02704 0.01808 -0.0438 0.5129 1.0000
7.000 0.9588 0.02654 0.01768 -0.0413 0.4803 1.0000
7.250 0.9736 0.02654 0.01773 -0.0386 0.4396 1.0000
7.500 0.9872 0.02681 0.01797 -0.0360 0.3927 1.0000
7.750 0.9970 0.02749 0.01849 -0.0334 0.3333 1.0000
8.000 1.0009 0.02881 0.01941 -0.0305 0.2600 1.0000
8.250 0.9977 0.03095 0.02100 -0.0275 0.1912 1.0000
8.500 0.9925 0.03334 0.02303 -0.0248 0.1474 1.0000
8.750 0.9888 0.03582 0.02524 -0.0225 0.1207 1.0000
9.000 0.9879 0.03827 0.02755 -0.0207 0.1042 1.0000
9.250 0.9897 0.04064 0.02987 -0.0192 0.0918 1.0000
9.500 0.9936 0.04293 0.03217 -0.0178 0.0817 1.0000
9.750 0.9991 0.04520 0.03438 -0.0165 0.0750 1.0000
10.000 1.0104 0.04712 0.03649 -0.0152 0.0678 1.0000
10.250 1.0222 0.04915 0.03850 -0.0140 0.0620 1.0000
10.500 1.0450 0.05083 0.04048 -0.0126 0.0568 1.0000
10.750 1.0653 0.05280 0.04251 -0.0116 0.0526 1.0000
11.000 1.0830 0.05526 0.04528 -0.0106 0.0488 1.0000
11.250 1.0963 0.05804 0.04840 -0.0097 0.0462 1.0000
11.500 1.1067 0.06118 0.05184 -0.0090 0.0446 1.0000
11.750 1.1114 0.06451 0.05544 -0.0084 0.0434 1.0000
12.000 1.1123 0.06797 0.05911 -0.0080 0.0423 1.0000
12.250 1.1116 0.07166 0.06297 -0.0078 0.0413 1.0000
12.500 1.1059 0.07595 0.06741 -0.0081 0.0405 1.0000
12.750 1.0906 0.08075 0.07253 -0.0091 0.0402 1.0000
13.000 1.0745 0.08602 0.07808 -0.0107 0.0401 1.0000
13.250 1.0565 0.09188 0.08418 -0.0131 0.0400 1.0000
13.500 1.0379 0.09830 0.09081 -0.0162 0.0401 1.0000
13.750 1.0190 0.10529 0.09798 -0.0200 0.0402 1.0000
14.000 1.0004 0.11280 0.10563 -0.0244 0.0404 1.0000
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Polar data table (+)
Polar graphs
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