FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-120 (fx79l120-il) Reynolds number: 100,000 Max Cl/Cd: 38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l120-il-100000-n5.txt Download as CSV file: xf-fx79l120-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7921 0.09996 0.09443 -0.0087 1.0000 0.0369
-13.250 -0.8338 0.08702 0.08136 -0.0175 1.0000 0.0360
-13.000 -0.8743 0.07647 0.07060 -0.0247 1.0000 0.0356
-12.750 -0.9026 0.06922 0.06313 -0.0290 1.0000 0.0354
-12.500 -0.9261 0.06334 0.05701 -0.0317 1.0000 0.0353
-12.250 -0.9471 0.05846 0.05187 -0.0332 1.0000 0.0358
-12.000 -0.9622 0.05454 0.04769 -0.0335 1.0000 0.0361
-11.750 -0.9759 0.05109 0.04394 -0.0328 1.0000 0.0366
-11.500 -0.9870 0.04801 0.04054 -0.0310 1.0000 0.0371
-11.250 -0.9943 0.04533 0.03749 -0.0285 1.0000 0.0377
-11.000 -0.9884 0.04307 0.03512 -0.0271 1.0000 0.0385
-10.750 -0.9790 0.04128 0.03324 -0.0258 1.0000 0.0394
-10.500 -0.9690 0.03979 0.03165 -0.0244 1.0000 0.0409
-10.250 -0.9579 0.03814 0.02980 -0.0230 1.0000 0.0425
-10.000 -0.9457 0.03633 0.02768 -0.0216 1.0000 0.0446
-9.750 -0.9306 0.03449 0.02555 -0.0203 1.0000 0.0462
-9.500 -0.9133 0.03293 0.02402 -0.0194 1.0000 0.0478
-9.250 -0.8963 0.03175 0.02278 -0.0184 1.0000 0.0501
-9.000 -0.8784 0.03053 0.02141 -0.0173 1.0000 0.0529
-8.750 -0.8590 0.02929 0.01992 -0.0162 1.0000 0.0555
-8.500 -0.8410 0.02798 0.01869 -0.0152 1.0000 0.0582
-8.250 -0.8223 0.02699 0.01767 -0.0141 1.0000 0.0617
-8.000 -0.8026 0.02601 0.01654 -0.0130 1.0000 0.0654
-7.750 -0.7845 0.02490 0.01544 -0.0118 1.0000 0.0689
-7.500 -0.7659 0.02401 0.01456 -0.0106 1.0000 0.0734
-7.000 -0.7290 0.02226 0.01278 -0.0079 1.0000 0.0839
-6.750 -0.7098 0.02153 0.01199 -0.0066 1.0000 0.0910
-6.500 -0.6923 0.02068 0.01121 -0.0052 1.0000 0.0985
-6.250 -0.6738 0.01994 0.01048 -0.0038 1.0000 0.1080
-6.000 -0.6556 0.01921 0.00980 -0.0023 1.0000 0.1210
-5.750 -0.6380 0.01845 0.00915 -0.0008 1.0000 0.1374
-5.500 -0.6208 0.01768 0.00852 0.0007 1.0000 0.1624
-5.250 -0.6048 0.01686 0.00794 0.0024 1.0000 0.1999
-5.000 -0.5903 0.01600 0.00742 0.0043 1.0000 0.2560
-4.750 -0.5777 0.01519 0.00707 0.0065 1.0000 0.3300
-4.500 -0.5516 0.01463 0.00688 0.0063 0.9833 0.4139
-4.250 -0.5147 0.01442 0.00683 0.0043 0.9641 0.4756
-4.000 -0.4765 0.01435 0.00679 0.0023 0.9463 0.5163
-3.750 -0.4380 0.01433 0.00673 0.0003 0.9290 0.5472
-3.500 -0.4014 0.01434 0.00667 -0.0012 0.9113 0.5740
-3.250 -0.3667 0.01438 0.00666 -0.0022 0.8940 0.5961
-3.000 -0.3343 0.01442 0.00664 -0.0027 0.8772 0.6158
-2.750 -0.3038 0.01445 0.00660 -0.0029 0.8613 0.6325
-2.500 -0.2745 0.01446 0.00654 -0.0028 0.8465 0.6463
-2.250 -0.2461 0.01445 0.00643 -0.0026 0.8329 0.6579
-2.000 -0.2190 0.01442 0.00632 -0.0022 0.8194 0.6687
-1.750 -0.1915 0.01439 0.00625 -0.0019 0.8071 0.6774
-1.500 -0.1642 0.01436 0.00613 -0.0016 0.7960 0.6872
-1.250 -0.1360 0.01433 0.00607 -0.0014 0.7855 0.6949
-1.000 -0.1091 0.01430 0.00598 -0.0011 0.7747 0.7041
-0.750 -0.0812 0.01428 0.00594 -0.0009 0.7656 0.7118
-0.500 -0.0544 0.01426 0.00589 -0.0006 0.7557 0.7208
-0.250 -0.0270 0.01425 0.00588 -0.0003 0.7466 0.7289
0.000 0.0000 0.01425 0.00586 0.0000 0.7378 0.7379
0.250 0.0271 0.01425 0.00588 0.0003 0.7289 0.7467
0.500 0.0545 0.01426 0.00589 0.0006 0.7208 0.7557
0.750 0.0813 0.01428 0.00594 0.0009 0.7118 0.7656
1.000 0.1092 0.01430 0.00598 0.0012 0.7039 0.7747
1.250 0.1360 0.01433 0.00607 0.0014 0.6949 0.7855
1.500 0.1643 0.01436 0.00612 0.0016 0.6872 0.7959
1.750 0.1915 0.01439 0.00625 0.0019 0.6774 0.8072
2.000 0.2191 0.01442 0.00632 0.0022 0.6687 0.8196
2.250 0.2461 0.01445 0.00643 0.0026 0.6578 0.8330
2.500 0.2745 0.01446 0.00653 0.0028 0.6461 0.8466
2.750 0.3039 0.01445 0.00660 0.0029 0.6326 0.8613
3.000 0.3343 0.01442 0.00664 0.0028 0.6158 0.8772
3.250 0.3667 0.01438 0.00666 0.0022 0.5959 0.8941
3.500 0.4014 0.01434 0.00667 0.0012 0.5737 0.9113
3.750 0.4381 0.01433 0.00673 -0.0003 0.5470 0.9290
4.000 0.4765 0.01435 0.00679 -0.0023 0.5155 0.9464
4.250 0.5149 0.01442 0.00683 -0.0043 0.4752 0.9643
4.500 0.5517 0.01463 0.00689 -0.0063 0.4135 0.9834
4.750 0.5776 0.01520 0.00707 -0.0064 0.3291 1.0000
5.000 0.5903 0.01600 0.00742 -0.0042 0.2555 1.0000
5.250 0.6048 0.01686 0.00794 -0.0024 0.1997 1.0000
5.500 0.6209 0.01769 0.00852 -0.0007 0.1623 1.0000
5.750 0.6380 0.01846 0.00915 0.0009 0.1374 1.0000
6.000 0.6555 0.01922 0.00980 0.0024 0.1207 1.0000
6.250 0.6738 0.01995 0.01048 0.0038 0.1079 1.0000
6.500 0.6923 0.02068 0.01121 0.0052 0.0983 1.0000
6.750 0.7099 0.02153 0.01199 0.0066 0.0908 1.0000
7.000 0.7291 0.02226 0.01278 0.0079 0.0837 1.0000
7.250 0.7462 0.02323 0.01365 0.0093 0.0786 1.0000
7.500 0.7659 0.02402 0.01457 0.0106 0.0733 1.0000
7.750 0.7845 0.02490 0.01544 0.0118 0.0687 1.0000
8.000 0.8027 0.02602 0.01655 0.0130 0.0654 1.0000
8.250 0.8224 0.02700 0.01767 0.0141 0.0616 1.0000
8.500 0.8411 0.02800 0.01870 0.0152 0.0581 1.0000
8.750 0.8592 0.02930 0.01992 0.0162 0.0555 1.0000
9.000 0.8785 0.03053 0.02141 0.0173 0.0527 1.0000
9.250 0.8964 0.03175 0.02278 0.0184 0.0500 1.0000
9.500 0.9135 0.03295 0.02403 0.0194 0.0478 1.0000
9.750 0.9308 0.03451 0.02557 0.0203 0.0461 1.0000
10.000 0.9457 0.03634 0.02770 0.0216 0.0445 1.0000
10.250 0.9583 0.03814 0.02980 0.0230 0.0425 1.0000
10.500 0.9692 0.03977 0.03162 0.0244 0.0408 1.0000
10.750 0.9792 0.04134 0.03331 0.0258 0.0395 1.0000
11.000 0.9888 0.04309 0.03514 0.0270 0.0385 1.0000
11.250 0.9946 0.04536 0.03752 0.0285 0.0378 1.0000
11.500 0.9877 0.04806 0.04058 0.0310 0.0372 1.0000
11.750 0.9764 0.05112 0.04397 0.0327 0.0366 1.0000
12.000 0.9624 0.05465 0.04781 0.0335 0.0361 1.0000
12.250 0.9453 0.05872 0.05215 0.0331 0.0356 1.0000
12.500 0.9268 0.06351 0.05719 0.0316 0.0356 1.0000
12.750 0.9025 0.06939 0.06331 0.0288 0.0354 1.0000
13.000 0.8748 0.07663 0.07076 0.0245 0.0358 1.0000
13.250 0.8370 0.08665 0.08099 0.0177 0.0362 1.0000
13.500 0.7910 0.10056 0.09504 0.0081 0.0369 1.0000
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