GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 50,000 Max Cl/Cd: 38.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795sm-il-50000-n5.txt Download as CSV file: xf-goe795sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4468 0.09730 0.09009 -0.0291 1.0000 0.0563
-8.500 -0.4487 0.09359 0.08646 -0.0301 1.0000 0.0548
-8.250 -0.4529 0.08990 0.08287 -0.0312 1.0000 0.0533
-8.000 -0.4611 0.08607 0.07914 -0.0325 1.0000 0.0519
-7.500 -0.4802 0.07471 0.06783 -0.0408 1.0000 0.0477
-7.250 -0.4800 0.07070 0.06381 -0.0411 1.0000 0.0475
-7.000 -0.4805 0.06635 0.05938 -0.0416 1.0000 0.0475
-6.750 -0.4802 0.06198 0.05486 -0.0420 1.0000 0.0476
-6.500 -0.4773 0.05824 0.05106 -0.0414 1.0000 0.0488
-6.250 -0.4681 0.05671 0.04960 -0.0397 1.0000 0.0517
-6.000 -0.4624 0.05295 0.04564 -0.0392 1.0000 0.0526
-5.750 -0.4553 0.04902 0.04142 -0.0386 1.0000 0.0531
-5.500 -0.4463 0.04516 0.03720 -0.0376 1.0000 0.0535
-5.250 -0.4350 0.04161 0.03323 -0.0364 1.0000 0.0542
-5.000 -0.4217 0.03840 0.02954 -0.0350 1.0000 0.0556
-4.750 -0.4063 0.03553 0.02600 -0.0334 1.0000 0.0595
-4.500 -0.3900 0.03320 0.02332 -0.0320 1.0000 0.0632
-4.250 -0.3718 0.03123 0.02103 -0.0306 1.0000 0.0661
-4.000 -0.3519 0.02932 0.01869 -0.0292 1.0000 0.0704
-3.750 -0.3320 0.02782 0.01687 -0.0279 1.0000 0.0772
-3.500 -0.3112 0.02651 0.01533 -0.0266 1.0000 0.0838
-3.250 -0.2890 0.02519 0.01375 -0.0254 1.0000 0.0901
-3.000 -0.2670 0.02435 0.01274 -0.0244 1.0000 0.1023
-2.750 -0.2436 0.02345 0.01174 -0.0237 1.0000 0.1125
-2.500 -0.2209 0.02279 0.01098 -0.0229 1.0000 0.1281
-2.250 -0.1988 0.02218 0.01041 -0.0221 1.0000 0.1485
-2.000 -0.1768 0.02160 0.00990 -0.0213 1.0000 0.1779
-1.750 -0.1551 0.02097 0.00953 -0.0206 1.0000 0.2423
-1.500 -0.1335 0.02012 0.00922 -0.0201 0.9997 0.3601
-1.250 -0.0712 0.01819 0.00905 -0.0261 1.0000 1.0000
-1.000 -0.0321 0.01851 0.00893 -0.0290 0.9915 1.0000
-0.750 0.0073 0.01886 0.00891 -0.0318 0.9831 1.0000
-0.500 0.0443 0.01914 0.00890 -0.0342 0.9735 1.0000
-0.250 0.0808 0.01942 0.00895 -0.0365 0.9638 1.0000
0.000 0.1188 0.01970 0.00902 -0.0389 0.9544 1.0000
0.250 0.1561 0.01996 0.00912 -0.0412 0.9445 1.0000
0.500 0.1905 0.02018 0.00922 -0.0429 0.9334 1.0000
0.750 0.2261 0.02039 0.00934 -0.0447 0.9223 1.0000
1.000 0.2632 0.02058 0.00946 -0.0468 0.9116 1.0000
1.250 0.3041 0.02071 0.00956 -0.0494 0.9016 1.0000
1.500 0.3390 0.02083 0.00968 -0.0508 0.8891 1.0000
1.750 0.3745 0.02092 0.00978 -0.0523 0.8765 1.0000
2.000 0.4104 0.02098 0.00988 -0.0537 0.8638 1.0000
2.250 0.4451 0.02103 0.00998 -0.0548 0.8507 1.0000
2.500 0.4790 0.02107 0.01012 -0.0557 0.8371 1.0000
2.750 0.5123 0.02109 0.01023 -0.0563 0.8228 1.0000
3.000 0.5451 0.02111 0.01035 -0.0568 0.8079 1.0000
3.250 0.5775 0.02111 0.01051 -0.0571 0.7923 1.0000
3.500 0.6101 0.02107 0.01060 -0.0573 0.7761 1.0000
3.750 0.6376 0.02114 0.01080 -0.0566 0.7569 1.0000
4.000 0.6663 0.02114 0.01095 -0.0560 0.7367 1.0000
4.250 0.6938 0.02115 0.01113 -0.0551 0.7141 1.0000
4.500 0.7211 0.02110 0.01121 -0.0539 0.6884 1.0000
4.750 0.7451 0.02111 0.01133 -0.0522 0.6576 1.0000
5.000 0.7688 0.02113 0.01141 -0.0503 0.6227 1.0000
5.250 0.7903 0.02126 0.01160 -0.0482 0.5841 1.0000
5.500 0.8109 0.02148 0.01188 -0.0460 0.5417 1.0000
5.750 0.8300 0.02182 0.01217 -0.0436 0.4951 1.0000
6.000 0.8467 0.02235 0.01259 -0.0410 0.4431 1.0000
6.250 0.8614 0.02308 0.01315 -0.0383 0.3871 1.0000
6.500 0.8735 0.02404 0.01388 -0.0355 0.3270 1.0000
6.750 0.8838 0.02524 0.01480 -0.0327 0.2641 1.0000
7.000 0.8932 0.02668 0.01597 -0.0300 0.2065 1.0000
7.250 0.9030 0.02831 0.01730 -0.0276 0.1617 1.0000
7.500 0.9135 0.03006 0.01884 -0.0254 0.1279 1.0000
7.750 0.9247 0.03185 0.02051 -0.0232 0.1024 1.0000
8.000 0.9384 0.03367 0.02237 -0.0213 0.0850 1.0000
8.250 0.9524 0.03543 0.02419 -0.0194 0.0719 1.0000
8.500 0.9696 0.03748 0.02627 -0.0179 0.0644 1.0000
8.750 0.9868 0.03937 0.02843 -0.0165 0.0566 1.0000
9.000 1.0050 0.04166 0.03089 -0.0153 0.0512 1.0000
9.250 1.0256 0.04440 0.03400 -0.0142 0.0478 1.0000
9.500 1.0400 0.04698 0.03682 -0.0127 0.0449 1.0000
9.750 1.0513 0.04981 0.03968 -0.0114 0.0422 1.0000
10.000 1.0551 0.05284 0.04329 -0.0089 0.0405 1.0000
10.250 1.0539 0.05604 0.04694 -0.0063 0.0387 1.0000
10.500 1.0483 0.05931 0.05055 -0.0035 0.0380 1.0000
10.750 1.0381 0.06277 0.05433 -0.0008 0.0377 1.0000
11.000 1.0245 0.06644 0.05828 0.0013 0.0375 1.0000
11.250 1.0080 0.07047 0.06257 0.0024 0.0375 1.0000
11.500 0.9885 0.07511 0.06743 0.0024 0.0376 1.0000
11.750 0.9669 0.08047 0.07299 0.0010 0.0378 1.0000
12.000 0.9438 0.08681 0.07949 -0.0018 0.0381 1.0000
12.250 0.9209 0.09410 0.08689 -0.0060 0.0387 1.0000
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Polar data table (+)
Polar graphs
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