FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 100,000 Max Cl/Cd: 35.92 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79l100-il-100000-n5.txt Download as CSV file: xf-fx79l100-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7401 0.09085 0.08566 -0.0056 1.0000 0.0301
-11.250 -0.7747 0.07827 0.07302 -0.0150 1.0000 0.0294
-11.000 -0.8082 0.06900 0.06360 -0.0220 1.0000 0.0286
-10.750 -0.8349 0.06263 0.05703 -0.0256 1.0000 0.0282
-10.500 -0.8554 0.05826 0.05246 -0.0265 1.0000 0.0286
-10.250 -0.8728 0.05458 0.04856 -0.0252 1.0000 0.0286
-10.000 -0.8843 0.05076 0.04443 -0.0236 1.0000 0.0289
-9.750 -0.8893 0.04711 0.04041 -0.0220 1.0000 0.0294
-9.500 -0.8887 0.04360 0.03649 -0.0204 1.0000 0.0300
-9.250 -0.8834 0.04034 0.03278 -0.0187 1.0000 0.0308
-9.000 -0.8741 0.03755 0.02945 -0.0170 1.0000 0.0322
-8.750 -0.8601 0.03535 0.02709 -0.0160 1.0000 0.0338
-8.500 -0.8433 0.03378 0.02541 -0.0150 1.0000 0.0356
-8.250 -0.8254 0.03193 0.02331 -0.0139 1.0000 0.0373
-8.000 -0.8060 0.03006 0.02114 -0.0128 1.0000 0.0394
-7.750 -0.7853 0.02863 0.01936 -0.0118 1.0000 0.0419
-7.500 -0.7656 0.02700 0.01778 -0.0109 1.0000 0.0446
-7.250 -0.7446 0.02575 0.01645 -0.0100 1.0000 0.0475
-7.000 -0.7232 0.02452 0.01508 -0.0090 1.0000 0.0506
-6.750 -0.7025 0.02336 0.01382 -0.0079 1.0000 0.0548
-6.500 -0.6820 0.02237 0.01284 -0.0069 1.0000 0.0591
-6.250 -0.6612 0.02142 0.01180 -0.0057 1.0000 0.0636
-6.000 -0.6415 0.02048 0.01089 -0.0045 1.0000 0.0700
-5.750 -0.6208 0.01971 0.01003 -0.0033 1.0000 0.0774
-5.500 -0.6014 0.01884 0.00919 -0.0021 1.0000 0.0858
-5.250 -0.5813 0.01808 0.00847 -0.0008 1.0000 0.0982
-5.000 -0.5614 0.01731 0.00777 0.0004 1.0000 0.1147
-4.750 -0.5420 0.01651 0.00712 0.0017 1.0000 0.1418
-4.500 -0.5237 0.01562 0.00651 0.0031 1.0000 0.1912
-4.250 -0.5078 0.01457 0.00595 0.0048 1.0000 0.2812
-4.000 -0.4926 0.01371 0.00570 0.0069 1.0000 0.3955
-3.750 -0.4744 0.01334 0.00562 0.0088 1.0000 0.4759
-3.500 -0.4549 0.01315 0.00556 0.0105 1.0000 0.5247
-3.250 -0.4356 0.01303 0.00549 0.0123 1.0000 0.5622
-3.000 -0.4113 0.01293 0.00542 0.0129 0.9914 0.5942
-2.750 -0.3742 0.01290 0.00541 0.0111 0.9739 0.6284
-2.500 -0.3366 0.01289 0.00540 0.0094 0.9572 0.6586
-2.250 -0.2991 0.01286 0.00538 0.0077 0.9405 0.6832
-2.000 -0.2612 0.01281 0.00529 0.0058 0.9237 0.7026
-1.750 -0.2234 0.01274 0.00516 0.0040 0.9072 0.7167
-1.500 -0.1870 0.01268 0.00505 0.0025 0.8908 0.7291
-1.250 -0.1525 0.01262 0.00495 0.0014 0.8742 0.7408
-1.000 -0.1200 0.01258 0.00485 0.0007 0.8578 0.7525
-0.750 -0.0894 0.01255 0.00477 0.0004 0.8422 0.7646
-0.500 -0.0593 0.01253 0.00473 0.0002 0.8275 0.7759
-0.250 -0.0297 0.01252 0.00470 0.0001 0.8135 0.7877
0.000 0.0000 0.01251 0.00469 0.0000 0.8003 0.8002
0.250 0.0296 0.01252 0.00470 -0.0001 0.7878 0.8136
0.500 0.0592 0.01253 0.00473 -0.0002 0.7759 0.8276
0.750 0.0893 0.01255 0.00477 -0.0004 0.7646 0.8424
1.000 0.1199 0.01258 0.00485 -0.0007 0.7525 0.8579
1.250 0.1524 0.01262 0.00495 -0.0014 0.7408 0.8741
1.500 0.1869 0.01268 0.00506 -0.0025 0.7293 0.8906
1.750 0.2235 0.01274 0.00516 -0.0041 0.7170 0.9073
2.000 0.2611 0.01281 0.00529 -0.0059 0.7025 0.9237
2.250 0.2990 0.01286 0.00538 -0.0077 0.6834 0.9404
2.500 0.3365 0.01288 0.00539 -0.0094 0.6586 0.9571
2.750 0.3739 0.01290 0.00540 -0.0111 0.6281 0.9738
3.000 0.4112 0.01293 0.00542 -0.0129 0.5943 0.9914
3.250 0.4356 0.01303 0.00549 -0.0123 0.5624 1.0000
3.500 0.4549 0.01315 0.00556 -0.0106 0.5251 1.0000
3.750 0.4743 0.01334 0.00562 -0.0088 0.4750 1.0000
4.000 0.4925 0.01371 0.00569 -0.0069 0.3949 1.0000
4.250 0.5077 0.01457 0.00594 -0.0048 0.2817 1.0000
4.500 0.5236 0.01562 0.00649 -0.0031 0.1908 1.0000
4.750 0.5420 0.01650 0.00712 -0.0018 0.1429 1.0000
5.000 0.5613 0.01731 0.00776 -0.0005 0.1145 1.0000
5.250 0.5812 0.01808 0.00847 0.0008 0.0982 1.0000
5.500 0.6012 0.01884 0.00920 0.0020 0.0860 1.0000
5.750 0.6207 0.01970 0.01003 0.0033 0.0776 1.0000
6.000 0.6415 0.02047 0.01087 0.0045 0.0702 1.0000
6.250 0.6610 0.02143 0.01179 0.0057 0.0641 1.0000
6.500 0.6820 0.02236 0.01284 0.0069 0.0592 1.0000
6.750 0.7025 0.02336 0.01383 0.0079 0.0550 1.0000
7.000 0.7231 0.02454 0.01510 0.0090 0.0506 1.0000
7.250 0.7446 0.02574 0.01645 0.0100 0.0474 1.0000
7.500 0.7656 0.02701 0.01779 0.0109 0.0446 1.0000
7.750 0.7852 0.02858 0.01933 0.0118 0.0417 1.0000
8.000 0.8058 0.03003 0.02113 0.0128 0.0390 1.0000
8.250 0.8252 0.03192 0.02331 0.0139 0.0371 1.0000
8.500 0.8431 0.03358 0.02518 0.0150 0.0351 1.0000
8.750 0.8601 0.03507 0.02673 0.0158 0.0333 1.0000
9.000 0.8731 0.03746 0.02945 0.0172 0.0315 1.0000
9.250 0.8831 0.04034 0.03280 0.0187 0.0305 1.0000
9.500 0.8881 0.04365 0.03656 0.0204 0.0297 1.0000
9.750 0.8889 0.04711 0.04042 0.0220 0.0291 1.0000
10.000 0.8840 0.05078 0.04445 0.0236 0.0287 1.0000
10.250 0.8731 0.05453 0.04850 0.0251 0.0284 1.0000
10.500 0.8552 0.05828 0.05248 0.0265 0.0285 1.0000
10.750 0.8316 0.06316 0.05758 0.0254 0.0284 1.0000
11.000 0.8060 0.06946 0.06406 0.0216 0.0288 1.0000
11.250 0.7743 0.07846 0.07321 0.0148 0.0293 1.0000
11.500 0.7368 0.09211 0.08692 0.0045 0.0299 1.0000
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Polar data table (+)
Polar graphs
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